150
r 4 4½.. .trr:tf . -Ic -- r - r TV,'- * -Ic - -r- - Best Avallaoiv?
r
4
4½..
.trr:�tf �.
-Ic --
�
r � - rTV,�'-� *
-Ic -�
�-�r�- -
Best Avallaoiv? �
bircuuty Classification
DOCUMENT CONTROL DATA. R & D"(Security classification of tItle, body of abstre ct end Indexing ainotation must be entered when the overall report to cleamilltsd
I. ORIGINATING ACTIVITY (Corporate author) a&, REPORT SEGURITY Cl-AISJFICATION;
Hughes Tool Co.-Aircraft Division UnclassifiedCulver City, California 2b. GROUP
S. REPORT TITLE
Aerodynamic Tests of an Operational OH-6A Helicopter in the Ames 40 ft X 80 ftWind Tunnel
4. OESCRIPTIVE NOT aS (Type ao report and Inclusive date@)
Final Report (June 1966 thru May 1970). . S. AU THORI S l (Flret name, m iddle initial, last nam e)
LaForge, S. V.Rohtert, R. E.
0. ;CPO'TDTE7-, M PO T DATy 9 74, TOTAL NO. OF PAGES 7b. NO. OF REFPMay 1970
e. CON TRACT OR GRANT NO. ia. ORIGINATOR *S REPORT NUMSER(I)
N~w66- 065 7- fV b. PROJECT NO. 369-A-8020
0. h.9b , OTHER REPORT NO(s) (Any other numbers that may be assignedthia report)
"d.10, DISTRIBUTION STATEMENT
it API-PIQVID FOR PUBLIO REIJ.AS3DISTRIBUJTIO UNLIMITE
It. SUPPL rEMENTARY NOTES 1i , SPONSORING MILITARY ACTIVITY
*.IANaval Air Systems Conmand
\This report precents a comparative evaluation of the aerodynamic characteristicsof an operational OH-6A helicopter as obtained from wind tunnel tests performedin the NASA-Ames 40X80 foot wind tunnel, flight tests, and digital computer st'udies.The objectives were: 1) Explore helicopter and rotor component stability deriva-tives and performance. 2) Simulate use of increased solidity by conducting aportion of the wind tunnel tests at values of thrust corresponding to v alves of0CT/V approximately one-half flight values. 3) Conduct analytical studiesinvolving use of digital computing techniques, 4) Measurement of rotor blade androtor mast moments.
DISTRIBUTION OF THIS DOCUMENT•'
•; l
"IS
UN LIM ITE D
DDUnclassifiedSerurity Classification
•; •1 ' •••'• :'.= ••'•"' '" *''": ...........................,,*.
:, •, • •..•., ,_,: .=, ••-,. ,=, ......... ••.,.., . ,.,
. .. . . . . . . . . .-. t-,..
REPRODUCTION QUALITY NOTICE
This document is the best quality available. The copy furnishedto DTIC contained pages that may have the following qualityproblems:
* Pages smaller or larger than normal.
* Pages with background color or light colored printing.
* Pages with small type or poor printing; and or
* Pages with continuous tone material or colorphotographs.
Due to various output media available these conditions may ormay not cause poor legibility in the microfiche or hardcopy outputyou receive.
E lIf this block is checked, the copy furnished to DTICcontained pages with color printing, that when reproduced inBlack and White, may change detail of the original copy.
security Classification m
Operational OH-6A helicopter.'
SeCUrity CISM~lification
b
1/
1J
HTC-AD Report No. 369-A-8020
AERODYNAMIC TESTS OF AN OPERATIONALOH-6A HELICOPTER IN THE AMES 40' x 80'
WIND TUNNEL
May 1970
Prepared Under Contract NOw66-0657-f
for
NAVAL AIR SYSTEMS COMMANDDEPARTMENT OF THE NAVY
This report has been reviewed by the Naval Air SystemsCommand. The findings in the report are those of thecontractor and not those of the Naval Air Systems Commandor the Department of the Navy.
APPR1VF.D FOR PUBLIC RZI4"t <~ IA 1 '
D1STRIBUTI5 UNILIMIM~-
DISTRIBUTION OF THIS DOCUMENT IS UNLIMITED
HUG S Tom COMPANY-AIRcRAFT DIVISION 369-A-8020MODEL REPORT NO. PAGEANALYSIS 9
PREPARED DY JLR E htr Aerodynamic Tests of an Operational OH-6A
3 CMECKEOvy S. V. LaForge Helicopter in the Amex 40' x 80' Wind Tunnel
TABLE OF CONTENTS
1. 0 SUMMARY 1
*1 2.0 CONCLUSIONS 2
"3.0 INTRODUCTION 4
4.0 NOMENCLATURE 6
4.1 Notation (Analytical) 64.2 Notation (Configuration) 7
5.0 DESCRIPTION OF TEST CONFIGURATION 9
5.1 Installation on Ames Supports 9"5.2 Tail Boom Support 105.3 Support Interference Configuration 125.4 Helicopter Control Console 135.5 Instrumentation 15
6.0 CALIBRATION AND DATA REDUCTION 17
6.1 Balance Calibration 176.2 Balance Data 176.3 Tail Boom Support Balance 186.4 Strain Gage Instrumentation 186.5 Position Calibration 19
7.0 TEST PROGRAM 20
7.1 Test Procedure 207.2 Test Variables 207.3 Test Log 21
8.0 DATA ANALYSIS 22
8.1 Method of Computing Theoretical Stability 22Data
8.2 Suitary of Measured and Theoretical 24Stability Derivatives
8.3 Rotor Flapping 278.4 Rotor Pitching Moment Derivatives 288.5 Thrust Derivative 288.6 Stabilizer Effectiveness with Angle of 29
Attack8.7 Roll Derivative with Angle of Attack 29
HuGHEs ToOm COMPANY-AIRCRAFT DIVISION 369-A-8020 -
ANALYSIS MODEL REPORT NO. PAGE
OREPARED BY R. Z. Rohtert Aerodynamic Tests of an Operational OH-6.A :cucEcKo my S. V. jaForge Helicopter in the Ames 401 x 80' Wind Tunnel
TABLE OF CONTENTS (continued)
8.8 Longitudinal Stick Motion Derivatives 308.9 Lateral Stick Motion Derivatives 318.10 Collective Stick Motion Derivatives 318.11 Speed Stability 328.12 Level Flight Performance 32A8.13 Loads Comparisms 32B8.14 Collective Control System Flexibility 338.15 Fuselage Characteristics 35
9.0 u1m gIS 36
TABLES
TABLE I - List of Oscillograph Recorded Data 38Channels
FIGURES
1. OH-6A Wind Tunnel Installation-Right Rear View 392. OI-6A Wind Tunnel Installation-Right Front View 403A. Side View - Test Configuration 413B. Front View - Support Tare Configuration 413C. Front View - Test Configuration 413D.. Three View Drawing 41A4. Schewtic, Side Vie' 425. Longitudinal Flapping, ale, Vs. Rotor Shaft 43
Angle of Attack,Osa6. Derivative of Longitudinal Pitch Vs. Rotor Shaft 44
Angle of Attack for Zero Flapping Vs. Advance Ratio7. Pitching Moment Coefficient Va. Rotor Shaft 45
Angle of Attack8. Derivative of Rotor Pitching Moment Vs. Rotor 46
Shaft Angle of Attack Vs. Advance Ratio9. Rotor Thrust Coefficient Vs. Rotor Shaft Angle 47
of Attack10. Derivative of Thrust Coefficient Vs. Rotor 48
Shaft Angle of Attack Vs. Advance Ratio11. Helicopter Pitching Momenit Vs. Rotor Shaft 49
Angle of Attack12. Derivative of Pitching Mome,.t Vs. Rotor Shaft 50
Angle of Attack Vs. Advance Ratio13. Roll Moment Coefficient Vs. Rotor Shaft Angle 51
of Attack14. Derivative of Rotor Roll Momsnt Coefficient Vs. 52Rotor Shaft Angle of Attack Vs. Advance Ratio
Transferred to C.G.
9 , 7 IW,
HUGHES TOOL COMPANY-AIRCRAFT DIVISION369-A-8a2oMODL _IEPoIT NO. PAGE
ANALYSI R. E. Rohtert Aer'dynamic Tests of an Operational OH-6AY .v. Laiorge Helicopter in the Ames 40' x 80' Wind TunnelSCHLZKKD 0 E
i ~ LIST OF FIGURES (continued)-
15. Longitudinal Flapping Vs. Long. Cyclic Motion 5316. Derivative of Long. Cyclic Flapping Va. Long. 54
Cyclic Motion Vs. Advance Ratio17. Derivative of Rotor Pitching Moment Vs, Long. 55
Cyclic Stick Vs. Advance Ratio Transferged to C.G.18. Helicopter Pitching Moment Vs. Long. Cyclic Notion 5619. Derivative of Helicopter Pitching Moment Coeffi- 57
cient Vs. Long. Cyclic Motion Vs. Advance Ratio20. Derivative of Thrust Vs. Long. Cyclic Motion 58
Vs. Advance Ratio21. Lateral Blade Flapping Vs. Lateral Cyclic Motion 5922. Roll Moment Vs. Lateral Cyclic Motion 6023. Derivative of Roll Moment Vs. Lateral Cyclic 61
Motion Va. Advance Ratio24. Long. Flapping Vs. Collective Pitch 6225. Lateral Flapping vs. Collective Pitch 6326. Pitching Moment Coefficient Vs. Advance Ratio 6427. Thrust Coefficient Vs. Advance Ratio 6528. Comparison of Level Flight Performance 6629. Comparison of Flight Teat and Wind Tunnel Loads 6730. Comparison of Flight Test and Wind Tunnel Loads 6831. Pitch Link Average Load Vs. Collective 6932. Console Collective Vs. Oscillograph Collective 7033. Fuselage Aerodynamic Characteristics 7134. Fuselage & Tail Aerodynamic Characteristics 7235. Time Histories of Rotor Loads 73
APPENDIX A
Tabulated Data A-1
APPENDIX B
Physical Description of Main Rotor and Controls B-1
APPENDIX C
Rotor Performance Sub-routine C-1
Rev. 7/15/71
HuGHM TOoM COMPANY-AIRCRAFT DIVISON~
PE ARE MY n tIn tet Igo Ia veil"e On an oe tOpeaioa O-
CHCE BY otp cE-6Aete heione tin the NA0A 180 Wind To 80'1
Helicopter and rotar coopoeat langitWUdil stability derivatives
ven detenimned fro the ezpez'lentai ataL and acmpared with
theetoal vslnes obtained from a digital oumputer prog'me,
Wbich inMrically oaLoAUJtes the aerodynamic abereeteriftiaS
of a lifting rotr,iusixag a strip analysis techniqua. thedry
siaspaes quite- well with most of the experimentally determined,
stabilityr derivatives. Specific exceptions awe discussed lit the
body of this report.
BelicaPter performance data eammured in the wind tunm1 ohmi
good ageuaent with flight data.
Ii In addition to the wind-tumel balance data,, blade and other
S ~helicopter Oc~on ents were strainl gaged for bending aomt data
~ 1Lad for control positions. Tests were conducted ove a oAA
ranig froe .25 to .140, plus limited data at,,* .144. thes
loads data shov good agreement with flight data.
these wind tunnel tests aind analyses were condi tod under contract
Now 66-0657-f .
HUGHES ToO COMPANY-AIRCRAFT DIVISION 369-A-8020ANALYSIS MODEL REPORT NO. PAGr 2
A erodyn•mc Teasts •f an operationl O- ----PREPARED DY_. E. ohert u Helicopter in the Ames 40' x 80' Wind Tunnel
' CHECKED BY S. V. LaFor2e
e l2.0 CONCLUSIONS
The results of the experimental and analytical investigations conducted
in this program indicate that numerical techniques can be used to predict
rotor stability derivatives. The agreement between computations and test
was excellent throughout the speed range investigated (/- .25 to .35).
It is felt that a simple computer program assuming uniform induced velocity
can successfully be used to obtain rotor derivatives at the advance ratios
tested.
The numerical technique was not programmed to predict the large increase
in blade flapping due to retreating tip stall. Though a program which
includes blade torsion as a degree of freedom and properly simulates the
shift in airfoil center of pressure with blade stall can be set up to pre-
diet the increased blade flapping, such a program would be eonsiderably
more costly than that presented in this paper. Comparison of the test
"date with the numerical analysis indicated that retreating tip stall did
not significantly change the pitching moment around the test helicopter
moment center. Although the hub moment was increased by the increased
blade flapping, the tilt of the rotor thrust vector woe concurrently de-
creased due to increased drag on the retreating side. Therefore, a more
sophisticated and costly program was not considered necessary to obtain
valid aircraft pitching moments about its moment center.
Derivatives of the wind tunnel pitching moment data with the horizontal
stabilizer both on and off were used to estimate the stabilizer effective-
ness and downwash. For unatalled conditions the downwash was found to
V 7M
HUGHES Tool COMPANY-AIRCRAFT DIVISION 369-A-8020
A SMODEL RPOT NO. PAGE 3
_____,_MY R. B.' Rohert Aerodynamic Teats of an Operational OH-6ASCNaCKED 3v . V. JEF5or-ge- Helicopter in the Ames 40' x 90' Wind Tunnel
be approximately 1.2 times the rotor induced velocity. This average value
as of comparable magnitude to those presented in the technical literature.
Rotor retreating tip stall reduced the effective rotor disc area, and
hence, increased the downwash velocity at the stabilizer.
Level flight performance as measured in the wind tunnel shows excellent
agreement with flight teat data obtained from a similar ship. Load@ date
.how good agreement with flight data.
~ 1
ii n
"9711" ' " ". . ",.
~ 370.......... ..
+J ANAL YSIS -.... O I "P0KPARtE . U. U hDk• AMy dR.Amic U"essts of ma OperZo~ • 01..-6A| €.CHCKED BY a-.V. 1100'W•L•p'AW in tbbm JOBS 40' X 80' Wind TWU19 e ,
"-J I "
13-0 M 'O
The Hughes Tool Company - Aircraft Divlsion..as conducted a v
I~ ~ mal test of an operaticm prototype . (K-.& beR4*qtOt,
[ ~SIN 62AW126s eqaipped vMt productioun bladeso in the X4A AMU
Il0ft. z B0ft, low Speed vind tume1, April 23 tbru OW~ 8, 106.
noe majar objectives of this test aewes Were:
L(1) Explore heliaopter and ror componenit stability aariv-
tives and pe-ti incluwdi establisbhmt of amV
L (2) siagAt. the use of inceased solidity by coamdwUlg
ia a portin of the n tunnel tests at valuss of thrust
ownespoing to values of "•/o" &ppruxintely one-half
current flight operationa values.
I(3) Oonduot analytiaal studies Involving the wse of digital
oamputing a ique for use in oamperisom vith the
vind tunnel. experimental date.
I (1) Nsas nt of rotor blade ma rotr support mat monment
for comparison with applicable theory mad cwrloation
Vith a6valable fliht test 4ata. HOvS IO• th seas 1-
tivity of the mast bending aent Inst-mntation vas
inadegquate for proper detemination of the bending
moma-ts oprodued by the inll flapping angle, and
thrust vector tilt encountered during the vind tunnel test.
.97041.
................ I I I I I I I I.I.
HuGm o HUN-IRRF DIVISIONANALYSIS- n- UMOEL ftp . PAea
PREPARED BY a . qtw Aerodusmic Test& of an opeational Oli-6ACHECKED MY~ ft. 7V. M ZaimsJleliccpter in the Ameis 41~~ x 80' W~nd Tum
hata plots* thulated reults,. and their analyseos IWIVAing
cqwisms vith applIceb1o tbecrisa, re3.Atve to the Aban
test objec-tives ane pesented. hwel. On test edvame ratios,
",ddM .25 to .400 used fmc the iajccity of the testfrm, ccswespa
to heliopt~fcrawed f24gt speeds of approximt.1Y 93 to 1514
knots. bdo data polmU. wene @@lletotd at/" 'A4 (169 k wO).
6=9 bavWrn s vwaee auc~tecl with tviel test seation roof
* ~~~damcs openad med closed. ftaes ver priaa'13y row' opertibma
ohmakAaut the b sllooplsandmitstion Prim to
operstion of tUe vin tiwnl. Swvpart toze and interfee
nina were ocaMted mid the data coccreoted for these effects.
.1704
IIJHUGHES Toom COMPANY-AIRCRAFT DIVISION 369-A-8020 6U M~yI...MODEL MiLPORY Nos, pAGg
PREPARED my R. E. ghet Aerodynamic Tests of an Operational ,.--CHICKED my S. V. LaIorge Helicopter In the Ames 40' x 80' Wind Tunnel
4.0 NOIENCLATURE
4.1 Notation (Analytical)
Ab 29.625 ft 2 , main rotor bled' area (4 blades)
A1 = Lateral cyclic blade angle, dog:#es. Positive is bladeleading edge down att= 0 9"
as Longitudinal til t of thrust vector, degree s. Aft tilt
is positive.
alLongitudinal flopping, degrees. Positive is blade tip
Seca down at co0e.Br 9 Longitudinal cyclic blade engle 4egreem. Positive is '
! B~sblade leading edge down at goo90.
S~~~bls aLateral• 0.flapping, degrees.\ Positive is blade tip down i
ba' Lateral tilt of thrust vector, degrees. Tilt to r~ight
is positive.
,C• Section lift coef ficient.
Cd - 'Section dreg coefficient.
CmLL q AbR
Ab R
%/• f Ab ( R)Z R
* ~C,
2 Aa, (flR) ZR
C Tr /a L0Ab (CIR)
2
Cx DCx V Ab;: (n•R)2
D - Drag, lbs,
L - Lift, lbs.
Rolling moment, lbs-ft.
'74 Rev. 7/15/71
HUGHES TOOL COMVPANY-AIRCRAFT DIVISION 369.*.kA80207
PREUPARED BY R. E. Rahtert Aerodynamic Testis of an Operational OH-6A
Nib
M Pitching Mome~nt, lbs-ft.
me " ~mnt center. All moment data were 'reduced about amoment center located at W.L. 36.43, F.S. 101.85, B.L. 0.0.This corresponds to the intersection of the' skewer pivotbell (pitch) axis with the mid-plane of the fuselage.
q 0CDynamic pressure, 1býi/ft 2.
R =13.165 ft, main rotor blade radius.
V1 a Tunnel speed, ft/sec.
CK Shaft (mast) angle, degrees.
X Inflow ratio.
p Density, sl~ug/ft3,
O b/rR .'0544, solidity ratio
.7Q Collective pitch angle, degrees.
.CR -T,.p speed, f t/sec.
4.2 Notation (Configuration)
B Main rotor blades (4). Rot~or disc -26.33 ft in diameter.Constant blade chord - .562 ft, NAiCA 0015, 9' washout.
F Model 369 (OH-6A) fuselage mounted on skewer throughxcargo compartment together with the Model 369 lower verti-1cal stabilizer attached to the, tail boom oupport (TBS).Lower vertical span - 27.5 inches from boom centerline, area
1.78 sq ft.
H Horizontal stabilizer. Chord -16.5 in., NACA 0015 airfoilsection, span 67 inches from boom centerlines, dihedral
-25 deg, area 7.68 sq ft,
K - Dummy skewer. Used only in conjunction with support.tare runs, to determine skewer interference corrections.
livMe. 7115/71
HucHEs ToOm COmPy- AIRCRAFT DIVISION 369-A-8020ANLYIS......MODIEL REPORT NO. PA09
PREAREO R. E. Rohtr - rodyiiamic Tests of an Operational OH-6AS.V. LForge Helicopter in the Amies 40' xc 80' Wind Tunnel
[R ft Main rotor hub.
jT wTail rotor. 2 blades. Rotor disk diameter - 4.25 ft.
V w Upper vertical stabilizer. Span 50.0 inches from~ boomn
£centerline, area 3.84 sq ft.
9" Rev. /15/7
HUGHES ToOm COMPANY-AIRCRAFT DIVISION 369A-8oANALYSIS L. T-LodN - MODEL REPORT NO. ,"AGE 9PRtEPAREDu NY - B_ R_ ,. Aerodynamic Tests of an Operational co-6AjCHECXKD my 51, - UsTm~ Helicopter in the Ames 40' x 80' Wind Tunnel
j~5 .0 MSMIPTlIM OF TEST COFIO_.AMI0M
proottype, sl 62-4216, was installed in the Ames 40' x 80' wind• ~t~ae3. on the t•Infel three - support external balance. Photo-
•aphs of this installation are presented in Pigs. 1 and 2.
As illJUtrated in these figures and the installation drawing.. (Fig. 3) the ship was supported on the two forwar-d (main) struts,
• Located cxi 1614" centers, by means of a 5" d~iameter skewer passing
thru the windows of the helicopter cargo compLiment. This
skewier was attached by a steel truss adapter to the underside
of the rotor mast base by means of the same four bolts which are
used to attach the mast base to the fuselage structure. The
helicopter pivoted about the center line of the 4" diameter ball
socket assely mounted stop each of the two forward struts.
2w center line of the 5" diameter skewer was 5.83" above the
ball centers, i.e., above the pitch axis. Wind shields were
provided around these forweArd struts. The protrusions above
the wlnd shields and the skewer itself were unshielded from the
wind. Correction for their effects were evaluated by the support
"tare rums which followed cmpletion of the production data
runs. The tMeahmmt of the two forward struts to the balance
system scales was suuh as to provide rea.outs of lift, dragi,
-.. rolling mment, yawing moent and side force.
•* .- 704
HUGHES TOOL COMPANY.-AIRCRAFT DIVISIONANALYSi MODE. L R911%4 NOL PAGE 10
PIA49PAfE * R.0E Rbhtwt -. Aerodynamic Tests of an Operational CH-6ACHECKED BY 3- V-oT " E' - lHelicopter in the Ames 40' x 80' Wind Tunnel
The instr.mntation and control actuator leads, the fuel line,
and C02 fire extinguisber line were run into the helicopter
thwu thie hollow skaew".
VFig. 3D preseuts a three-view drawlng of the OH-6A.
5.2 , S
The least count of the Ames pitch balance thru the tail strut
"was too large to provide meaningful pitching moment data fo the O-
6A hielicopter configuration. Consequently ITM-AD personnel
desiged and fabricated a two-component strain gage balance of
adequate sensitivity for the determination of the pitching moment.
the IW3C-AD Tail Boom Support (23S) is shown best in figure 1,
"connecting the Ames tail strut to the helicopter tail support
pivot.
The RTC-AD Tail Boom Support performed two additional functions.
Ffrst, the spring (50 lbs./in.) and damper (standard OH-6A lag
dsmper) combination eliminated the ground resonance problems
associated with attaching tie tail boom directly to the massive
Ames tail strut. Second, as the load on the TBS spring changed
dixing a test run, the fuselage angle of attack changed from the
nominal value which had previously been set by the Ames tunnel
operator by means of appropriate positioning of the Ames tail
strut. The linear actuator, cont~rolled by the HT-AD console
operatco was used to provide vernier readJustment of the fuselage
angle of attack.
1.
HUGHES TOOL COMPANY-AIRCRAFT DIVISION 802MODELRE~
ANAYSI R.L. l-00 ýa*PAGE 1I ,R.AmEDa.y R-. r. R.nht.w-t .rodyn•n•c Tests of an Operational o,0-6A
cHIEcKEo BY S.. •Helicopter in the Amen 40, x 80' Wind Tnnel .
15.2 TfRoi BomSprt, (Continued)
I mutt (=Let) sigl.e of attack 4)was fed digitally into the
Awms data acquisition system in conjunction with the external
I'I
ba~lance readings,, exclusive of pitching mom~ent. In addition
Ic< was manually recorded by the helicopter control console
operator.
1 ,70
'• L 704
i HUGHES TOOL COMPANY-AIRCRAFT DIVISIONANALYSIS R. - ?•MOPREPRED Y it 1RhtdI Aerodynaic Tests of an Opertiona OH6A
CHECKED BY .2.V Raze-f I Helicopter in the Am 41 80'
5.3 &ww_ Interference Cnfiguration
In .,der to detearmine a correction to account for the interference
of the skover support during the production data te.ts, an
auieliary support was ut'ilized as Illustrated in figure 3s. Data
were collected over a range of Pc at two dynamic pressures,
horizontal stabilizer on and off, with and without a dm= skewer
Sinstalled. The incremental effect due to the presence of the skewer
was used as a correction in the Ames balace data reduction
progprs., and to the pitching mnent data obtained from the ail
Boom Support balance. 2he pitching moment correction vas muai.
I9
*5
1~
S ';: • 704
--. ,i- -. -- * --
HUGHES ToOL COMPANY-AIRCRAFT DIVISIONANALYSI - BL_ Floo MODEL REPOP•.V AIE 13PREPARED gy R.U. aohtert Aerodynamic Tests of an Operational OH-6AcH.cKEDoBY B. V. wow Helicopter in the Ames 40 1 x 80' Wind Tnnel
fTe helicoptw control console, designed ard fabricated by
NTC-AD0, v located in the wind tunnel control room so as to
provide optmzwn coodination between the wind tunnel operators
and the helicopter operators. This control console provided
remote ontrol and monitoring of the helicopter. For operating
effectivness, it was divided into two adjacent panels: The
left being the Flight Control Operator's Station; the right,
the Engine Control Operator's Station.
At the Flight Control Station were those switches and panel
"monitaring instruments required for establishing aircraft angle
of attack, tail support angle of attack, lateral cyclic position,
longitudinal cyclic position, and pedal position. In addition,
there were instrents for monitoring the lateral flapping and the
longitudinal flapping. An oscillograph record switch was also located
on this panel. However, duing actual test operations, the oscil-
logaphs were operated and monitored by HTV-AD personnel who
marked the applicable data point number on each record as it
waz taken.
"The Engine Control Station had the switches for 11OV AC power,
fuel valve starter, throttle, 1N2 beeper, end collective. Panel
instruments were provided for monitoring collective position,
970
• ". ................. ............ ..... ..... ".....,,................_.... .... ,...., ...., ......................... .......... . .,............ "..........'". -
HUGHES To00. COMPANY-AIRCRAFT DIVISIONMODELFt EP&;A. 0O PACE 1ANALYSIS- R. L. 13M _ý MO
PRtPAfED SY It. R. Rnhta. t c Tests of an Operational CKE6AcNEcxtolV • V mye.•£ Illelopter in the Amues 40' x 801 Wind Tuanwl
$.4 Helicogtr •Cotro:, Console (Continued)
throttle, N 2 , rotor rzpm, NI, VTT, torque, DC Bus amperes, engine
ruming-time clock, engine oil pressure, and engine oil tamp-
ermtue. Panel warning lights were provided as monitors of
M transmission oil pressur.e, oil temperature, and chip, 'mtrsnmissaon chip, engine chip, and fuel clog.
Both the Flight Control Operator and the Engine Control Operator
maintained a running log of the operational data on his respective
console coded to the Run Number and Data Point Number. In addi-
tion the 50 channel oscillograph record nmwber was logged.
'The layout of the panels on the control console are detailed
on the Ref. I. drawing.
The primary rotor controls, collective, loLaitudinal cyclic, and
I lateral cyclic, were variable and powered by electrically driven
screw jacks mounted in the cockpit. The rotor power and speed
were controlled through the engine fuel control and the engine
,, governor*. There was a remote "beeper" switch on the control
console to change the governor rpm setpoint.
I 9-iiiE .o
11
HUGHES ToOL COMPANY-AIRCRAFT DIVISIONANA LYSIS 'MODEL REPOA "Z
80 PAGE 15
PREPAREDO By R •lht.t Aerodynamic Tests of an Operational aR-6ACHECKED BY . V. Ts'oRCg"e Helicopter in the Ames 40' x 80' Wind Tunnel
5.5 Instruentation
In addition to the Awa external balance data, up to 53 channels
of oscillograph data were recorded throughout the test on two[ oscillogaphs, one of 50 channels, the other of 18 channels
dfrectwriting. The latter was used to monitor during each run
"significant load values, principally pitch link load, mast
longitudinal bending and tail boom vertical bending to insure
that the aircraft was not being subjected to excessive loads.
The list of the oscillograph recorded data channels is presented
in Table I. Main rotor data obannels, i.e., items 1 thru 17
of this Table, in addition to blade flapping position, required
use of a multi-channel slip ring assembly mounted atop the
rotor mast assembly. The electrical leads from the stator side
of the slip ring assembly were fed down thru the hollow mast.
Mast bending strain Gage leads did not require use of the slip
ring since on the (8-"A kellcopter the m•at is f1Xed, the drive
shaft rotating inside the mast to drive the rotor blades. The
rotor blade loads are transferred thru two main bearings to the
fixed mast.
The outputs of the control position potentiometers were fed to
the control console meters as well as to the oscillograph. A
blade flapping resolver was installed on blade No. 1. The re-
solver was mechanically constructed so that its flapping readout
I D4
HUGHES TOOL COMPANY-AIRCRAFT DIVISION369-A-8020YMODEL . nREPORT NO. PAGE 16
,*vPREPARED V It. E. Rohtert lAerodynamic Tests of an Operational OH-6A
SCHECKED BY. S. V. LeForge iHelicopter in the Ames 40! x 80' Wind Tunnel,
5.5 Instrumentation ", Continued)
." was not affected by extension of the blade retention straps
under centrifugal loading adr by feathering nor by lead lag motion
of the blade. Suitable electronic circuitry was provided to
rnsolve longitudinal flopping and lateral flapping and thus
give a direct continuous reading on the two respective meters
i+ located on the control console. In addition, the output of the
flapping resolver potentimeter was recorded on channel 22 of
the 50 channel oacillograph.
In parallel with the HTC-AD oscillographs, several of the data
channels mre recorded on magnetic tape for subsequent automated
data reduction by NASA-Ames personnel.
[i
Ii
iii
L *74 Key. 7(I1711
HuGHEs TOOL C OPANY-AIRCRAFT DIVISIONý ..A..oW
ANALYSIS ..-. In a n MODEL 'r NO. PAGE 17
PREPARE D MY- R_ nhtA.•t -- Ae'rodmmic Tests of an Operattonal @-6ACHECKED §V. a. V. TPgcu, f_,blicopter in the Ames 40' x 80' Wind Tunnel
6.o. _ _ A .UM RMLTION
6.1 %I~anoe Osalibktion:
fe t re-supaa't ex0ter balance of the 40' x 80' ft. wind
LI titnel had been previol callbrat~d by NASA - AMES personnel
p in accordance with the -AMM standard procedures.
[ .6.2 al, ce Data:
Ba.lance date, were red.ued in acez'dance with the NASA - AM
standard crnputer propx Weight toe corrections and support
I, interference tare corr ct ons based on the support interference
runs were Incorporated in the data reduction program. Me final
HASA reduoed data wre available in a tabulated format
appropriately coded pe rn number ,and data point nuber.
Pitching Moelnt Data omthe AMS three - support external bal-
&we is not usable. It had been established in conferences
between AMS and HIV-A •rsonnel prior to the test that the
least count of the AME 4iace was too great to achieve
meaningful accuracy in pitch data. Consequently in lieu of
the AMES balance, the I hing monent data were obtained by
means of an W C-AD des ed and fabricated strain gage balane on
the tail boom support,
The NAMA reduced data *aesented in Appendix A, pages A-1
through A-51.
974 Rev. 7715/71-
HUGHES ToOl COMPANY-AIRCRAIT DIVISIONANALYSIS L-20 MODEL R 1--2 PAGG 1PREPA•E•tE .my 1t3.- t _ _ Aerodn'• eic Tests of an Oper.tional Cm-6ACNKCmC my S, V, I1"=fte Helicopter ~nthe Ames 40' x 180' Wind tunnl
6.3 TAU DOGS Suit orb Dalane
Because of the ack of sensitivity of the AMES pitch balanc i,
=-AD designed a tvo comonent strain -a;e balance on the 1tai_.
bom su8pcpt. This balance measured the uxial and normal foces
'e• at the tail pivot attacbment point. Readout was onohanne3
8 and 9 of the MC-AD 18 - channel oech In adt anthese date we~re record•ed in parallel on ti"•:.q tape. MU• tape I
S . ~data were reduced by the AMS cocmputer p• ~~ and treanmi, ted
:.to MC- in tabulsar foovat. Sufficient oecillograph data points .i. vecreread a• -AD to establish the 'va~l dit, of the aumtd :
7.,• reduction. The AMES values wer~e then used to compute the ýItch-
3.
,g moments about the helicopter pitch • is.
ttap
"Pitchese. at a w , da werec i rel for eight tares anddappt interference prior to conversion to the coe muiclte d ormt
41 t used in the data p re ation graphs. V ule are tobulaph d a n pages
e-52 through A-55 of Appendix A.
""ftlibration of the tai boom support boa rce was conducte(ý overthe appldc.ble L Soad range in the -D ldorstory wprie th o the-
•tunnel test. Standard osoillogreph R-C• pronedures wez4' usedm athroughout the a eltal test.
S6.4 S'terain (1ae rumntationz
Phe strain g dae instrumentation listed f Tle I was ,,, ed
apt p-AD pritr to shipment to the hel e opten to the wi tm l.
Since this insatarentation was phs. V1cato that used on a fullge
17
A-52 Chrough A-5 if Appedii iii ip
HLGHE• TOOL CO .MPANY- AIRCRAFT DIVISION $6.-A-.o -I ~ ~ANALYSIS ,.MOEMrpqN.
PAE"! -
: PIEPARIED BYB Te-t of an c•mst-ona
lWt
10eIw M V- i• the Ames 40, xc ino u awl
instrumeamnd flight test klicoptar,, standard cailibration pro-cedures wie employed by f-AD calibration and electronic personnel.
Standard pscillogaph R i. procedures were used throughout the
ifatual t" t.
6.5 Position ;tibraltions:
Following installation in the wiznd tiunel, with the helicopter
set at zero, wind of,# final calibrations were conducted for
all posit Lon potenticmet's utilizing a precision in$llnmter
or scale r required. Mue oscillog-aph readouts and control
oosole readings were suImtaneously recorded against the in-
cllnomeU (or scale) re&d ings.
Ir
1.
IiIiI
3704r
HUGHEs TomL COMPANY-AIRCR rr DmVSION 6-80 2
ANALYSIS- MOE 4pok O AEP
PREPARED BY R. Z. 1Rohtert AairodYrAni Tests of an Operstiami (E-6ACHECKED my S. V. Lamcre Relicopter in \tk Awes 401 '8 IS Wind ftwel
A cczplete log~ of the tunnel test rms,, th, oscillogaph data
recordso Wn tabulated reduced data for 'Ut test series ar
available in tbao .=-AD Technical Departme t files. !wsnty-tbr'ee 'data runs (470 data points)., four suppor are ~mm (52 data Points),
andl seven static veight twoe runs were madi'.. Helicopter engine
operating time vas 35.*7 hours. Tunýel occi i ncludling
setup and teardown vs24 shifts. The tur el operated ona two
shif'ts perday basis, 5 daysu/eek.
5i II HUGI ES ToOL COMPANY-AiRCRAFT DIVISION 36 -A 8o2o
P~PIAPZD gy R. E. Rloer Aerodynamic Teste of an Opir raionsl OI-C.____E ____11_____1E9 Helicopter in the Amex 40' x 0' Wind Tunnel
8.0 DATh ANALYSIS
8.1 •:thod oý Computing Theoretical Stability Data.
iTs theoetical method used herein to compute stabili erivatives
I i mslainpi and is inexpensive to run. The comparisons f theory and
t at dats show excellent agreement. Consequently it 1 elt that
ti is co puting method is adequate for simple helicoptlrs of modest
a ad -0.35). Some of the test data show eviden aif retreating
t!P sta i. For these the agreement with theory is on y sir. A
I f w dam points were run atyA - 0.4. These data are quite scat-
tred dad the agreement with theory is marginal.
Týe the pretical stability dots used to compare with ta y ind tunnel
test doe were obtained by means of a digital compute p ogram,
b sed o References 2 and 3, which numerically calcul ted the oero-
dynamic characteristics of the lifting rotor using th assumption of
uniform induced velocity and ignoring the effects of blide flexi-
lility. This program employed a strip analysis in cc piting the aero-
"ynamic forces on the blades. The aerodynamic forces, In conjunction
ith ce trifugal, inertial, and weight forces are coai ed to solve
or the blade flapping. Knowing the flapping, the 1c a=. blade
angle cf attack and the aerodynamic forces for a tri•i cndition are
#btain d. The angle of attack and Mach number of each, ocal blade
ectios together with the tabulated blade character iti s determine
he se•etion c and Cd. The lift, drag, and torque if ach section
a the computed.
_ _.. -... .{ f ..'
HUGHES ToOL COMPANY-AIRCRAFT DIVISION 369-A-8020MODEL REPORT NO. PAGE 23
ANAI!VYSi E Aerodynamic Teats of an Operational OH-6APlRl[PANl[Y *.I 'oher - Helicopter in the Ames 40' x 80' Wind TunnelCHECKED my S. V. LaForge
Since the rotor blades of the test helicopter incorporated the MACA
0015 airfoil section, the tabulated values of C and Cd were ob-
tained from the data of Reference 6. This reference presents C2
and Cd as a function of angle of attack and Mach number. These
"coefficients were synthesized from hovering data of a rotor with a
0015 airfoil section.
In addition to the blade section aerodynamic characteristics and the
physical characteristics of the rotor, the other inputs to the
computer program include: collective (00.75), longitudinal and
lateral cyclic pitch (BIs, A1 e), Inflow ratio (\), and advance
ratio • ).
The outputs are longitudinal and lateral flapping (a1 and bls),
thrust, hub moment, thrust vector tilt (a'. and b',), and shaft angle
of attack (0< s).
In performing the wind tunnel test the cyclic control was positioned
so that the aircraft was trinmmed to zero longitudinal flapping angle,
-is. In the digital computations this trim condition was obtained
by holding the collective pitch at the corresponding test value and
varying the longitudinal cyclic pitch, BIs, and inflow ratio, >1
to achieve the test values of thrust and zero flapping. After the
trim condition was obtained, small perturbations were made in the
proper parameters to compute the derivatives. Since shaft angle,-.•s,
is an output, dn iteration has to be made to hold'< constant when
IA' I?* I I.i
HUhmn ToOm COMPANY-AIRCRAFT DIVISION 369-A-8020ANALYSIS MODEL NEPORT NO. PAct 24PRPARKA RV. otert Aerodynamic Tests of an Operational OH-6AcH•E• Eo a 8. V. Lelorge Helicopter in the Ames 40' x 80' Wind Tunnel
obtaining the derivatives with respect to control positions and,.0
Page 25 presents a flow diagram describing each step in the iteration.
41, Additional details of the computer program are described in Appendix C.
Figure 4 shows a schematic side view of the test setup. All moments
were measured around the moment center shown. Therefore, the cal-
culated hub moments and shears were transferred to the moment center
for comparison with wind tunnel data.
8.2 Sumaery of Measured and Theoretical Stability Derivatives
The following table suranarizes the rotor stability derivatives obtained
during the wind tunnel test and compares them with computed deriva-
A. tivee. The more important longitudinal derivatives are discussed in
detail in later sections of this paper.
The derivatives with respect to collective and cyclic stick were ob-
tained using the stick motions measured at the console. Plots of
console collective pitch angle vs blade angle measured on the cecil-
lograph record show that the flexibility of the control system re-
duces the angle of the blade by 117. to 14%. The cyclic stick is more
than twice as flexible as the collective stick (stiffness of 7000
ln-lb/.ad as compared with 16,370 in-lb/red for collective), so it is
expected that the cyclic angle at the blade would be reduced 25% to
31%. The deflection of the control system is a function of the
pitch link load; therefore, the difference between the console measured
angle and the blade angle is a function of flight condition.
HUGHES ToOm COMPANY-AIRCRAFT DIViSION 369-A-8020MODEL REPORT NO. PAOE 25ANALYVSIS L
PREPARED my R. E. Rohtert Aerodynamic Tests of an Operational OH-6A
CHECKEDo.. S. V. LaForge Helicopter in the Ames 40' x 80' Wind Tunnel
X - X P+yax I'.l -r~ etors
Where X ta 011t of (B| ,the F oklowwl P,&rameteri • hb' "Tr~ q Ub X b
,75 1 "1S, AIs, u b
First Etimuate
Rotor n tk.. m • \ Subrouti.oSerformance OuPori r]&h
SSubroutine
Ouutputb a .C' , [
";" •an1 I = (al*)l "(et.)5
o.db ".I ~ i ~ ~ 1
T-, (as-ab) e O,
Compute Rotor C~~~OtpuCt,.q .0C~(1
•Zm __Cm- -mb
Sre, ,-(6• 6)b
4 -00 obtT oi-r
nd N.Compute Rotor -"-- CTpeq) < 0. 05C (81,4 01,lb
Derivatives 12 - X'b 4 4k
Em, Cw"Clb
b a AXI" Etc
i, / Rotor
Pe rfla r ] fob,4X Completed S
P"All Other Inputs aamtr
Roto yes Output
11krom, n (AT'Z ... ZA
u40I'-T &Isj, We8 iET CTZ" CT b
Comliat•.r Rotor I-a• •~ I It, . 0 SolveDerivatives for
bo Mg lA-o b 1b X r . T_
"- .$ ,... .. •,,, -- . . .,,• _ _...._._ . - .. .. ..
tiUGM TOOL COMPANY.AIRCRM~ DsIVION 369-A-8020MOPIL REPORT "a. PA~t 26
PeP to LmyA Ig I ahte:t ,nrodynsuic Tests of a Operational OK6AcNZcKsos by, S. V. ILo~orlig Helicopter in the Amts 40' x 80' Wind Tunnel
TALEX 1. 8TUBILtT RlWIATLVWS
Li 0.25 i 0.30 u w 0.35
Derivative Test Theory Test Theory Test Theory
ba /bas, deg/deg 0. 15 0.14 0.32 0.20 0.25 0.Z8
S CrIoi/;Js,/deg 0.00014 0.00013 0.00019 0.00018 0.00025 0.00024
0.005 /deg ,'.OO 00056 O.0065 .0.0069 0.0086 0.0086
6 C /a/ ,,/deg 0.00009 -0. 00004 0.00010 -0. 00005 0. 000ZS -0. 00004
Alal /4 B1 s, deg/deg -0.98 -1.17 -1.08 -1.Z3 -1.25 -1.36
BC /0 i/BI/deg -0.0009 -0.0013 -0.0009 -0.0013 -0.0010 -0.0014
6 Cý/o/,B 1 , Ideg 0,0040 0.0056 0.0048 0.0070 0.0058 0.0082a
aC /016Ag i /deg 0.0008 0.001Z 0.0008 0.0011 0.0009 0.0011S
6A /'a0.75' deg/deg 0.60 0.82 0.76 0.96 1.35 1.43a
6C /a/b, 0.014 0.013 0.015 0.015 0.007 0.010
"This table shows good agreemnt between theory and test in the speed
stability and the derivatives with angle of attack, except for the
derivative of roll moment with angle of attack. These test data show
hysteresis and the differences have not been resolved. The theo-
retical derivatives with collective pitch are 11% to 14% high and the
derivatives with cyclic pitch are 25% to 31% high due to the flexi-
bility in the control system. It can be seen from the table that
when the control system flexibility is accounted for, there is good
agreement between theory and test.
1__
HUmID TooL COMPANY-ARCRAfr DIVIS 369-A-8020 G,UOL miar NO. -PAQ9 27
AN ALYIS
PM9PAMRB If 14. 19. I@httrt Aerodymnmic Toots of an Operational OI-6AC4CKeDS s V . Ial7ue - Helicopter in the Anse 40 x 80 Wind Tunnel
8.3 Lot
rigure 5 presents a plot of longitudinal blade flapping versus shaft
angle of attack. The theory, shown as a dashed line, coipared veryi~jwall a!tA ft 0.25, but deviated from taet at the higher values oý^7he theoretical retreating tip angle of attack is printed next to
the trim point. O- point (0-,A 0.35)and 80.75 " 10') has a
1 zretreating tip angle of attack vell into the stalled region. This
"teot point shows the effect of stall in increasing the change in
blade flapping with shaft angle of attack, Stall reduces the lift
On the retreating blade and also shifts the airfoil center of pros-
I. sure towerds the trailing edge which tends to tyist the blade nose
down. Both of thee effects increase flapping. The theoretical
progrim accounted for the decrease in lift but assumed rigid blades.
Therefore, the effect of dynamic twisting of the blade could not be
- determined.
ligure 6 presents a plot of the change in longitudinal cyclic pitch
vith change in shaft angle of attack to maintain zero flipping.
The values of d l/ , from test dats are somewhat greater
than theory. The values of Big were obtained from stick position
Sam measured in the cockpit. Due to the flexibility of the control
system, the actual values of B, at the rotor are less than thea
Svalues calculated based on the static calibration. Flexibility ue
discussed in section 8.2.
0 W. 771377
u TOOL COMP A .P-.R=Ar, DIVISION 369-A-80204.,4-L IMPORT NO. PAct 28
PANPALYS 1 at. . htart Asrodynow'ia Tests of an Operational Oii-6A
C9CK6e OSV..0. V'. 'IaForge Holicop,*.r i. the Ames 40' x 80' Wind Tunnel
8.4 Rotor Pitchimn &cnmant Derivatives
Figure 7 presents a plot of rotor pitching moment versus shaft angle
of attack. The test points were obtained by subtroctiug the moment
due to fuselage and rotor hub from the total pitching moent; thus,
they represent the moment due to blades only (except for blade-
fuselage interference which should be small).
L Figure 8 presents derivaitives of ) 7 obtained by reading the
slopes of Figure 7. The agreement between theory and Qest is excel-
l lent. At a.75 a 100,1• 0.35 the agreement with test is good
1•! even thogh the measured flapping ims considerably greater than
theory. This point to in the retreating tip stall region, which
increases the dreg on the retreating blade and tends to reduce the
aft tilt of the rotor thrust vector. Therefore, when the umeunt is
*1 transferred to the test moment center (aircraft center of gravity),
the increased nose up moment due to increased flapping is offset
by the reduced moment due to reduced thrust vector tilt. At, A-w 0.4
there is a considerable amount of scatter in both the flapping and
pitching moment date points, so the comparison of theory with test
r' • data is inconclusive.
8.5 Thrust Deriv&tive
Figure 9 presents C'T/C" vs8o< for the values of advance ratios
teasted both horizontal stabilizer on and off. Figure 10 presents
[ the derivative C4 CT'* vs AA. These derivatives were ob-
ING ev. 7715 M
II l~usHum TOOL COMPAnY-AIRCRAFT DVISON 369-A-80200O"L • O• .N*. 29
ANALYSISSPRZ .O SPY .. E. Igohtrt Aerodynamic Tests of on Oerational O,-6A
.ECceD y 8. V. loHelicopter In the Ames 40' x 80' Wind Tunnel
tained from the slopes of the curves in Figure 9. Theory is also
- shown on figure 10 and is in excellent agreament with test data.
8.6 Stablizer Iffectiveness with Anjle of Attack
Figure 11 prements pitching m at data for the complete helicopter
in the form of C/u" vs'(* with the horizontal stabilizer "on" and
"off". Figure 12 presents the slopes of the data in the form of
0' as a function of.A' . (At,^- 0.4, there are uo
data "horizontal-on".) This figure wea used to estimate the ratio
of actual to theoretical davnwash at the horizontal stabilizer. At
"044 of .25 and .30, this ratio is equal to 1.2. At/,4. - .35, the
ratio is 1.0 for the unstalled test and 2.8 for the test conducted
with retreating tip stall. Rotor stall reduces the effective rotor
disc area, and hence, increases the downwea•h velocity. Thus, the
high value of induced velocity can be expected. The value of induced
velocity ratio of 1.2 is almost identical to the measured ratio
presented in Figure 33 of Reference 7. This reference presents
data obtained from a wake survey of the induced flow near a rotor.
8.7 Roll Derivative vith Anale of Attack
Figure 13 presents C /r- ve -e 6 for various conditions. Figure
14 presents the roll derivative with shaft angle as a function ofA..
The theory shown does not agree with the test. The theoretical
derivative of lateral flapping b, vs rotor shaft angle, 4W8, is
: ipositive, but the theoretical derivative of lateral thrust vector
9M0 Rev. 1131
III- Sb'}iM. . .
HuE ToOm CoMPAY-AIRCRAFT DivISoN 369-A-8020MOEL REPORT NO. PAaa 30
ANALY898pMpeAR* M IL. E. l.ohtert - Aerodynamic Tests of an Operational OH-6AC HK ED $. V. LaForge - Helicopter in the Ames 40 ' x 80' Wind Tunas
tilt, bWe ve 0<a is negative, therefore, when the moment was
transferred to the CG, the total became negative. The difference
between theory and test is unexplained but is probably due to the
low sensitivity of the balance system in relationship to the small
helicopter rolling moments.
8.8 onyAtutdinl Btick Notion Derivatives
Figure 15 presents a plot of longitudinal flapping angle a1 with
incremsntal longitudinal cyclic pitch , determined from longi-
tudinal stick motion. Figure 16 presents the flapping derivative
|de as a function of,^ . The test data indicate the flapping, due
to stick motion, is less than theory. This is attributed to the
flexibility in the control system. The longitudinal cyclic pitch
system flexibility is approximately twice that of the collective
system (sae 8.2).
Figure 17 presents pitching moment vs AB 1 , horizontal stabilizer
'off". The theory is also shown on this Figure. Figure 18 presents
pitching moment vs &Bla, horizontal stabilizer "on". Figure 19
presents 3Cm obtained from the slopes of figures 17 and 18, and
also shows the theory. As expected, the test is lower than the
theory, due to the flexibility of the control system. Figure 19
r shows that the derivative __ becomes more negative with the
horizontal stabilizer on. This is due to the change in downwash at
the stabilizer, which is a function of aCT '# . The derivative
[- " ] ... i .. .. "R.. ...ev........ 7/1...5 71.... "i" ... "•l ! I 1 1
HuaHES ToOm COMPANY-AIRCRAFT DIVISION 369-A-8020MooeL IMPoRT Mo. PAst 31AM ALYSISI..,.,,,.-o , : E. R.ohtert Aerodynamic Tests of an Operational 0H-6A
C t D D, s. v. Iyor jHelicopter in the Awes 40' x 80' Wind Tunne
"CT I haincreasea withl,.d ; therefore, the difference in moment,
stabiltzer on versus off, should increase with forward speed.
7.giura 19 shows this trend, but the absolute value of the difference
due to the stabilizer appears high. Figure 20 presents 4CT /1"[) B1ev both theory and teat. The test results are less than the
theory due to the control system flexibility.
8.9 Lateral Stiek eotion DerivativesIFigures 21 and 22 present lateral flapping, bta, and rolling moment,
respectively, as a function of incremental lateral cyclic
pitch, &Al.. Figure 23 presents the derivative of rolling moment
with lateral cyclic pitch • taken from Figure 22. Due to
flexibility in the lateral control system the test flapping and roll
moments are less than theory. Both the theory and the test indicated
"the rolling moment derivative is independent of Q at a given value of
advance ratio,...4
8.10 Collective St-ick gtion. Derivatives
Figures 24 and 25 present longitudinal flapping al. and lateral
flapping ble vs 00.75- As discussed earlier, the flexibility of the
control system results in a reduction in the angle of attack change
at the rotor. It is expected that the theory will be 11% to 14%
greater than test. This is true except for the run atA- 0.35.
The trim points have a theoretical retreating tip angle of attack of
11.2° which is into the stall region. As stall tends to increase
49704 Rev. 7715171
HUWrs TOOL COMPANY-AIRCRAFT DIVISION 369-A-8020I MODEL REPONT NO. PAOu 32PREPANEO DY R. E.. Rohtert I Aerodynamic Tests of an Operational OH-6A
CHECKEDDY S. V. Worge Helicopter in the Ames 40' x 80' Wind Tunnel
the derivative of flapping with collective pitch, this effect offsets
the reduction due to control system flexibility.
8.11 Saeed Stability
Figures 26 and 27 present Cm/c and CT'/Ga vu..e respectively. These
tests were conducted with the horizontal stabilizer installed. The
variation ofh ws obtained by changing rotor speed, rather than
tunnel speed. Consequently, the stabilizer lift is affected only by
the change in downvash due to the change in rotor thrust. The thrust
derivative is small; therefore, the effect of the stabilizer on the
pitching moment derivative is also small.
The speed stability agreement, as shown in Figure 26, is very good,
As noted previously, the case of/- - 0.35, 907 10 degrees, is
well into retreating tip stall, which increases the drag on the
retreating side, resulting in a forward increment of tilt of the
thrust vector. The moment change due to the change in thrust vector
tilt appears to be greater than the moment change due to increased
flapping, causing an unstable variation of pitching moment with,.,.
The theoretical retreating tip angle of the/4 - 0.35, Q 0.7.5' 8
degrees point is equal to 20 degrees. Thus, the stall is even greater
than the -0.7.5 1 10 degrees point discussed earlier. As expected,
the slope of this case deviates from theory to a greater extent.
T
II
K HuGHEs ToOm COPANY-AiRCRAFT IDIISION'M .LS . o]em•OOKL ftEPO•,T O. •AGE 3LAANALYSIS MODE L.P 0 PAG 32
PREPARD* .BY Aeodr±c Tests of an 4vpetiu0m Cl--aCHECKEODY ,. , U.Taen,, e.licopter in the Naen 10' x 80' Wind !iumel
Figur 27 iniae theowry imd vstinates byr a
amount. Tetest vabms of Cr4±meincixe the danlqmd
on the atabilizrw tbrf ore., test data Im"1xdes a anai.
ten that is naglected in the theory.
8. Level Flight PerfrMace.
FYw helicopter level fl3ght, the thrust is equml to the weight
and the zepulsive force =zt eqml the drag. T condition
inotained wben CX 2 badTh ti point
fr eachl•4 tested was obtained crosplots of 0 and oc
to obtain the rotor pover coefficient CP 50~j3 HP ef ore
this *o=3 be dme, CX bad to be corrected for the tare of the
tail vppcrt. Also, in order to ecmpe vith fli*t
pow inmmsi emmats contained in referewe 8, the drag of the
instrunentatiao vire pack, Ubich mas not I2al1y*d in the
tare 8upptrt setup, had to be reved. This drag was estimated
tc be one sque foot of parasite area. A compariso at
"o =.2 ponds,,_r R f ft/sec, and f: .0023o6, is shown
in:-figure 28. These data show excellent agreant with the.
fl dta 6&U ,.reference 8.
Best Available Copy
________________
H UGHES TOOL COMPANY-AIRCRAFT "V".SIUNANALYSIS-- . PAGE 32B
PREPAREDBY A___ It. Aeroxynmt of ant 'operational cH-6.A,C.ECED " Helicpte.- in -h Am, 40' x 80' Wind TInne
8. •aw L C•.r"uom
Ccpsm pploto are prese•ted for the rai.n rotor blade 15%
f3lavise cyclic berlding and main rotor pitch link cyclic load
as wtai=i from the wind t-rma I test and from recent fligh t
testa. Both sets of loads data are plotted as fctimos
OfrWU and C,2l0`9
EIanation of figure 29, 15% flapwise cyclic bending, shovs
m izatter i• the wind tunnel data, but no yronunced trend
with either Cp/4 or Va. The flight test data also show
scatter which is generally typical of thic type of flight
test data. The data do show reLaogele agrement. T flight
test data avere at a eavhatt. h led 1evel than do the
wind tmel dta. Bywever, stice the flight test data are
grouped at the higher values of C, and C/,, this result
1s not unexpected. It is sigjiicant to note that the endurance
limit was not exceeded fcw any test condition including the
highb/- of the wind tiu&,el test (equivalent to a forward opeed
of 154 k)mots, 2 points at 169 knots).
Eznii tion of figure 30, pitch link cyclic loads, shows
gene,-..,v less scatter than the blade bending m=cent data.
Otherwise, the conc ons arion are similar to those above.
Time histories of rotor loada as obtained fro-m flight test and frcxo
wind tem.n-l test are pr:-.nted in Fig. 35. lber.. is fair agree-
Stw = he-o sBofest Ava' able COPY
-Hwu TOOL COMPAY-AIRCRFr DIVISON--I ANAL.YSS •, K.. IL• 1?l 1f, -- .. .
,ARWA , ,Y 1 . i. godtr .... b ne iests of an operational W-.- c,,cRE Ay -. V. ] , a12 me Helicopter in the Awe 40, x 80' WiMA Ycuel.__ ,_._-__.___,_-
/
8.14 Collective Control System Flexibility
The values of collective engle,Q 0 4 5 , as used herein are those
read at the console, i e., a direct function of cockpit stick
position. Frop HTC-,D oscillograph records, the pitch link
average load has been read or selected runs and plotted in
Figure 3ýl as a function ofQ0 ..7 5 at the console. The slopes of•" dP
the lines faired thru these date pcints, i.e., d- oconsolef
have been used in conjunction with the value of collective
.etol syt sti essp -6,370 in-lbs/radian, to calculate
the expected cban e in blade angle as read by the potentio-
mt, on the blade feathering axis and recorded on the oscil-A,
For eaple at/I 0.25
Q f __ x._ ý.06:in. x 57.3 4.P lbs , .100
console bol-t0 onored.
S9 console X &Oco61e O• o-.i3.1ow. p
d~console
~ : n a ialaiAr man~e values of dconsole of 1.13 and 1.14
9" .Rev. 7/15/751
HUGHES Tomt CotAPANY-AiRcRAFT DIViSION 9Q
C~CBe 11R. .Taig 1 e~~ptar in tb- Ama 4 0 x 80r 'wind T-=e 14
wzre detamu±z f(,A /a 0 0310 and./1 a 6. 35 zmesPective1.Y.
Mume -~~w boe, been utilized in fairixg te I Ines tbra
%b Crrlmde dUplat of? Fiue 32 w" reets
Ye1 ~ M n kig into accmt the scatt~r in tbase
dats, the agenient between the slopes deeuzw priaa
an discussd Abn n the aettal 4 , is quite stisfact~m-
72*xibilityr be& been discussed above =de &12...
dest Available Cop
I; AA SHUGHES TOOL COMPANY-AIRCRAFT DIVISION 369-A-8020ANLYI R.ot L.Fod OE. - -RPORT NO. P~ce 35•npa, po sy RL. 2. R~oht•rt Aerodynami.c Tests of an Operatio~nal OH-6A
c•a g€ . .olly 8. V. ol.orge Helicopter in the Am*e 40' I 80' Wind Tunnel
II 8.15 Fuselage Characteristics
Plots of lift Coefficient (CL) and pitching moment coefficient
(CV*) are presented in Figures 33 and 34 for the Rotor Off
Configuration. These figures also present data collected in a
1/3 scale model of the helicopter in the Northrop/Noreir wind
tunnel (Ref. 4). The pitching moment curves are in good agree-
msnt for both horizontal stabilizer on and off. The Ames data
show a slightly reduced slope for CL vereusCmi in both coses,
am well as a negative shift in the angle for zero lift, which
is unexpectedly large for horizontal stabilizer off. Figure 33
also presents a computed value of pitching moment based on the
Multhopp body formula of reference 5 for a fuselage fineness
ration of 2.3, i.e.:
Cm* - 2-- K- L2. . 47 y * - .007228. l Abil .2-8.7 v '***
This slope is somewhat higher than those shown by the full scale
date and the Ref. 4 date. The Ref. 4 data were collected on a
1/3 scale model tooted at a IN/ft. corresponding to that of a
full scale ship at 55 knots.
U .SI
SHUGHmS TOOL COMPANY-AIRCRAFT DIVISION "A MODEL REPORT NO. PAGE -6ANALYS,,S... ... ,
PRKPARED By R. X.- RdhtAt Aerodynamic Tests of an Operational o*6ACHECKED MY S. V. lab= Belicopter in the JAs 40' x 80' Wind Te=1
9.0 Lin Or
1. =4rAD Vfwin 39- ', Ca.2. Camisole Ileyout-
2. RACA 51 3366, "A Ifthod fer ftudying the Tnaient lade-
?l.apping Bebaviev of Lifting Rotors at Excum~e Operating
odItmesm," Vy Alfred Oeswe and A' D. aim, Gated
Jw==Y 1955
3. ACA, T 3747,, "Equations and Procedures fo Numerically
Calculating the Aerodynamic Characteristics of Lifting
Rotos," by Alfred Genowi, dated october 1956
4. Report E-.AD 369.-8o1.2 "Aerodynamic Tests of a 1/3 Scale
Model 369 A Helicopter at Narthrop/Nozrir Wind Twmel - Test
Series No. 9," April 1967
5., Perkins and Hage, "Afrplwne Performance, St•ability and
Cut rol," MA. 5-26, page 226
6. MACA 21 4356, "llffect. of C urssibility an Raotr Havering
Perfawlmze ad Syntbesized Blade-Section Chaacteristics
Derived Measured Raor Perf ornice of Blades Haing
_IVA 0015 Ainfoai Tip Sectt s", by Jams P Shivers a0d
Pa-l J. 0,rpenter, dated Septmer 1958
m4
ANALSISHuGmE ToL. COMPANY-AIRCRAFT DIVISION PG
PREIPAREDO NY ~ .3II ~CHECKEDS myA
7. ~ ~ I OPa - (ci Amvisw oaion vth mvw r)
So.3.e !,m84" b7 SMY 11. NUs~, dated Apri 1956.
- 8. I== ftvojet 1b. 4-3-0250-.51/52/53,, Ngrt Two of fft
Pte,~ Resport of the MW~Ihnegf n1&%t 29st, Pertfcaoce
Pb&M at the Cu-" U.11copter.. Ubzued (Cleow) and Av=A
with the Un-7 or U-8 Weapon Bubsystw@0 19.S. AkW Avlastiem
-~~ lest Aattvity, Uilmow Afl, Califainia, dated Aagust 19&1.
r4
SHUGms ToOm COMPANY.AIRCRAFT DIVISION 3696A-802oMODEL REPORT NO. PAGE 38
ANALYSIS• __.__.rodna_ Tests of an Operati-ial Ow-6f
RCHECKEDY I Helicopter in the Ama 409 X 80' Wind Tunnel
TAMZ I
List of OsaLli9nrah Icordod data ,QPs agan a
50 Channel 18 MemanelItem Oscillograph Direct-Writing Osaillograph
1 M/1 Blade, Flopwise Bending, 15% 1
2 M/1. Blade, Flepwise Sending, 17% 2 -
3 M/i Blade, Flopwise lending, 301 3
4 /i Blade., Flepwie Sending, 507 4
5 M/S. Slade, Flaplifse lending, 701 5
6 (spare) -
"7 M/1 Blade, Chordvise Bending, 17% 6 -
8 M/i Blade, Cbordvise Bending, 507. 7 -
"9 K/i Drive Shaft Bending, No. 1 810 X/1t Drive Shaft lending, No. 2 9-
•,11 X/& Drive Shaft .Torque 10 -
12 MA/ Pitch Li~nk load -- 2
13 MIR• Festhering Bearing Support,
Tension 12
14 M/R Blade Retentian Strap, Tension - 16 (s)
15 M/i Blade Retention Strap, Bending - 3
16 M/i Lead-Lag Position 15 -
17 M/R Angle Position, Feathering 16 -
18 /IR Mast Laterel Bending(outside upper) 17
19 1M/R Mast Lateral Bending(outside lower) 4
20 X/R Mast Longitudinal Bending(outside upqper) 19
21 M/R Mast Longitudinal Bending(outside lower) 5
22 M/I Mast Lateral Bending (inside) 20
23 M/I Mast Longitudinal Bending(inside) 21
ma : (a) For run 3 only, CH.16 was long. accel. and CH. 17wae lateral accel.
... •,•_• •704
HUGHES TOOL. COMPANY-AIRCRAFT DMSMO 36-82
ANLSSMODEL REPORT NO. PAGM
PREPARED BY odyuamis Tonts of am Operational IG
&I. CHECKED NY alisopter In the Am* 40' 1 80' Wind Tumia
so Giatmal to Channel
24 Longitudinal Conitrol 1,1r, &md -6
25 SmL1 Acceleration at e.g. -7
26 Ship's Airsped 26
27 Engine Torque Pressure 27
2.8 Longitudinal Cyclic Position 28-
29 Lateral OyIelic Positimn 29
30 Rudder Pedal Position 30-
31 Collective Poseition 31
32 Throttle Poseition 3233 Tail loom, Support, Azial Load 8
34 Tail Boom Support, Vertical Load - 935 Tail toomn Support, Position 33 -
36 Tail Doom Vertical lending, 1Forward 1
37 Tail Doom Horizountal Sending,Perlward 1
38 Tail loomi Torque, forward -12
39 Tail DOom Verttc~1 bending, Aft -13
40 Tail Boom Horizental Bending, Aft -14
41 Tail loom Torque, Aft -15
42 Upper Vertigal Stabilizer,Lateral lending 34
43 Upper Vertical Stabilizer, LateralBending (near root) 35
44 Horizontal Stabilizer, Plepuriselending (near root) 36, 41 (b),
45 Horizontal Stabilizer, Flapviselending (near strut attaeh4) 37
46 Horizontal Saiie hrwsBending 38-
&ag~: (b) M1L36 shifted to CU. 41 (4-17-68)
~1-A.1....
HUGHES TOOL COMPANY-AIRCRAFT DIVISION •t.•.ee•o i'!•I .ootL ,-,o•T ,o. ,Ao•
,.L•,,,. ee ) i'
hlJ•W•r JJ t•e •,' •
JaN BOO V• t•mel
$4) Obanmol 18 G•mal •:
It• • 9L3:sc•-Wr/.t• Onctllol•aph "JSasxlaSUs el• •, _ ,•-
&,? liorls4m•l S=abtlinr |g:ru¢
/844 39 -
.• • m (t per '€•) S0 - :S•9 likmmur !'oeition (ehipaC) 60 - i:---
:" •lel•tM hNl•m• 22
;" 5•, Ilmllo IF[4WIpdLwI •@eltlen •rm:rlq•J• •otmt•m•e= •3 -
, •2 2S.I:Lnl Code •8 -vii, 53 21sial 0040 17 (a)
!
ti l•o: I•1 •r t•m 3 rely, •B. 16 mo lens, aeeol, and; C•l. 17 gee liters1 ae•ol.i"
Ir 1
!
e• 'i
, I i I I I I I . . .... . . . .. .. o ,, ... . r
. . ...... .
0: -- Rih:- c~74
Page 40
Figure 2. OH-6A Wind Tunnel Installation -Right-Front View
.44" 1
LL
LL~ 0
Lii (D 0u N). CLi
cm V~0
n wI U) I
0 w
U)w ~ LL
0w
00
00 f-
-' 0-
2u
a CLi
CLL
0a)
Q. k.
I-3.1
3.1
Page 41a
II
,'L 4)
-i i • ,
•! i, I
S I -I
, HUGHES TOOL COMPANY-AIRCRAFT DIVISION 369-A-8eoANALSI .,MODEL REPORT NO. PAGE 42
SJPARED S Aerodynamic Tests of an Operational OH-6AcHEcKco my- 8, V. T, I Salicopter in the Ames 40' x 80' Wind Tunnel
i~i
T
,i
V.L. 83.00
h 388ft.,Tlt of ibart vith reerotLi ,3.8ft. fo usege cm :3*
momentcenter
V.,. 36.43 Ad ---
d 4* .92 ft.
Fa" .
[ ~Page' 43~
Q1 'ji
__ _ __ _
*ý 4.:
U.L
to !
Ls :z
~ V)f*. a '*%tj*
z viJ
on r
Pagei44
' Ii
I I, " !
!• F I++7jj ... ..- ......
* .!L: .- • .--•,o ... ... !... . . . . . .: '
ItoI.,.
*1-• . I '
4U
\ -
S ..... 7 I .. "
- . . ...L -_ ,J ..- .I.-II " I a l Ii i I IKT - - - - -I./
I ~Page 4+5
II
44_ _ _ _ _ _
Ow,
LO
J4
LL; L
vuQ
44 ~~ ____ ____4
"I 04
r-,-
Page 46
4 i
::, . .- , , ' ': ; . :•! i, ',i ' "i, "
. ....... .I ,
, .
-. ..
__ - .-j"
r-q ~~~~i - - ~. ... ...: , ,....... ..-........... . ,. . r-: .. ..1 .. - .. r T ,.. .. .. . .q .r
.: • , • -:--• - -• -I- , . :. L -..4--+ -: . . -L- -l. . 'I.: , .. . ! . t :
V I ,I
I -'--"
.
-CC
• 4Ii . -i' . I "
... .. _ . . . ... . ... _ . -j.. , '. I '/ -
Ill • ' ' : . I )!'
S•. •,.. . . .I.. ... _ , .. . . . . . . .. . . ... . . . I -.-..4-...|
S- • : .!;. •. 4 - ; .. 1-.-. . -: .~ . I . .*• ; '' • / : '
.t ' q t / ; I •" I -1 n , "I / '.
1 ! " , "i, [ •r" .. .t - .. t ' .. '-[ , ..
..
' ,
' i : ' , i;;t
' 'I: I :I"...
.. ..i L. . . _ .. - I .L J...L . ..., . . -4. .. . ' . . *-, . -1,: .- .
Page 47
. .~.. ..
14'B
iA -r
0
.0
FIG 3
page 4~8
-T I
IS
K' tl
I ~ I I I ....
LL,,
_ -4-
r I7
'A.~
____ I -0
Page 49
V,-..". .*
Li1
4t *jt 4 .-.
- >1
4ico2.
It Fl&, 1
Page 50
IIE
LIL'
in Ini
'~~~L 6i 74ll~
.1-0 - 1
-1 Page 513
il* " __
, ._ _ _ _ _ 0
12~'IU
"L U. U.'
Li0.0' A. . 0:
1 .
-- *•.4 . .
L � Page 52
11 .:. ,
I, I
Ii .( .... -�
� .
I -
S. V -.
(JL���mb - I :. II
¶ 4 I'I
I) *1I
I,�. ... L1*
- I'.1 II
IIt . . IiI -.
.1
-� 0 Ii lr
I�I 9 -ftj0
I�I
FIG. I'I-
4.
Page 53
4 ,
LLL UI.;
- ,F16I IS
Pag 54
.4 4 -1 ...... .
Li %.
l~Fl G.
.I
~bi Page 55
7-. 7 -71
I. 4 .
N~~'
7-1f
>~
..... .. .... .. ...
Page 56
2?. N.. L
'~.
. ........
I J .I
IihiPae5
ALI'' -At--.- - -
041,
t4 4 I L
L 4,
U-. u..
.: ... . . . . . . . . . . . . . . . . . . . . .. . *,'di
K . .FIG.
! • -2 t •Page 58
I
I.• i [' ,.W Ji
I . , •..,.
,
I .
" II I I 'I•II
- I•"- .:• "- -I ....... i"i....,j...,..... .. .. . . ... :" ... .. .V.1 • ! . , I:
1 ; ! * ,S..,..'.. ..
. ..
!- .. . [-.... .
._I .~
.. •
€ .. . ... .-.I i .. i ;
. I:. • . .. . . ' 4 '4*
.;.. .. *.. " -. . . . .
...
4'
•.. .
.
... ".. . . . ..... 4' ': . " '
|S ,& i I. ,
I,,, -i , .- .'.,- -.. '-....
4 .. ; '•
F''
SI
I '
I . _ -ti. .• - - 1 ..
I"~Page
59
-, -;1",- -\4
FIG
Page 60
*t T
4-V
4- -~. -~ -L -L I-
-1 - -
T- 1 G.2?.
page 61
F. 11 I,
-1,
I Ifii
ow Iiiiu
I,, II11-II
1F 1G,. 23~
Page 62
L - L
IL-Z 1i Ol-
vs%
- rt.
-.ti
.11 4I
'F~F G , 2 -T
,I
t Page 64
ýL _._ .. . - -"
77
'-444T ,I WTtt
1- --I
r in"
I:..'-1*
"" _1,-. ,
-- 4-
' I "-
L-I
0 -,,, - .-.. ..
! _-T t*; t
T•' I ... -- -t -- . .~.. .-. I, , ,I i._
-F G .... .. - ..... -- ', ---.-
m i .. .3,I : -
F w ! I t I 'I
I i --- .~.1I + - - i
-4'l-; ' " '
I.I
117i ... :
FI G, 2•
Page 65
t~[ %t M~
tt
f
4
T 'i
ff.i10 W [I1
Wt:
4 41i&+
I-. -. Page 66
91
14W Af. 4r 0. 9MAC
-7I
.4-4-4-4
1 ~ T17
U003- -7-
........ ....... .... U.... .RPM
A.:FIG Z8 I.
Page 67/
:Fl _ A I ~ I
.4.77
*.:jm 4 T~~L 1tiL J -Al L ... l- 3 -1 .. ...
- I 7
r ~+2
-- 7 T .i._ fo_ T
I ~~~-ider '~-i~'-
7-- - 4 41 7 -.;, 3 0 -J
F1G. 29
Page 67
T-7
717±
17 ,.2
~ --oý2 4-
--777
.... ..... ~... ---
__
7 1
F:.1
Td-,
j~1...~ :LILII -.I_ __
t.4
j
'~ ~~~~r
29'~-i~.4~~A .
page 68
41 -. t
ido
COS~ O. -- 0 .1..*
LLF 5 30 R94.32-6
Page69 '
I , Q,
I4 J
T',
11__ _
tit s Iiiro oLin
0, -7 ?4. V ;4, P l dF
13 ~ Page 70
H B -.. ~ - .- -- I jij- K :.
- I'4ii7L7~lp _ .+>~j Kt:7 K
t . ..
I I I 'I
4- I t"
LJ>.r
~zbo~v -Page 71
L .. ..... .... 4. -AA
-4- t
- .-.-.4. -. ..... 1
4'7
LII
gifF/ G. 3
Page 72
* 7747
-7- -
I...! wi 7. '-. >
t-
ý4I
t'7IMAMj4 -4i L-H
F/ r, 3'
TIME HISTORIES OF ROTOR LOADS
Ames Wind Tunnel Data, I= 0. 349, CT/a s 0. 0843
.. .. .. . .. .. . ............................. Flight Test Data, L = 0. 344, CT/(T 0. 0894
Main Rotor Pitch Link Load6040 . /'I\ /
-4;0 .. .. "' 1
Main Rotor Blade - 17% Chordwise Bending5000
4000 %
in-lb 20 0
\/ \,, ...\' % Y*
0
Main Rotor Blade - 15% Flapwise Bending
It j".. I*. / A
1 , . \\ J1400
80;
tO0
(I I 0 I I I ... .'4 , ,I
ReProducdrorna vailable copy.
ETC -AD Report 3'69-A- 1020
IonWN&
rv-.0 ýo len "o in'o;d% P-- "0 W% .0 .0 W% 46;1-
tit X, V10 Z I"
:f" .0 Ito 4 cp FýIv- 0ý W,
f^ In do 00%to Wk 10 IN .4 wif^ 01 'o C% 4w in fn r'1
ui 10 0 Q'C c "D a qr'ý:O W% 0 10 4 0:0 .4 10 C% -4) r'P 4 c
0 C)C%.O jel CLI 9 '100
0:^ CO.ý3 up I it I it
"it- 06 ýo fft mi .0 4CP! in r- F- #'%! . 0 '.; 4) 4
.4409%6 01 0% ca GO 14Pý rm '0 (21.40 P-1 -4' -11 It QD WN P_ UN cr P. r-
94 1" -il f" 0 -1Lij 0.451 401.1 1-0 0
4) L% 45 too Oc.
o.14% .0-00" #A CY-1- '4! -il 0, - 7 Z-A ww & 4^ J V- IV 0- cc N a W .0 4cp m 0-0 .0 40 P- I% G. 'r.
0 m;o 0 0'M LjI 43 Z, C_. 1-0 C; o;
ck ift Ij a c c%
Uhx kn 01
;Igo %A m 0ý 11 4",Z., -4 44 ITI ILK
us WN N OD 'rl- 9% 'N ^ 71 0 f-j w o. 4.-1; 0 f- ý4-c -3 f" 0 1 -0 0 C 0 C. Ir 0 0 C14-1. :0 0 N cý12. Q 6) ;140 C% -01
0 00*c: 9 813$ i; 03 - O:C-
-7 -- ; 1 4CIO
tf% 10 - (Y' -& .'o I" .ýP- In 4e% to, mlN .0 0 ýr 0.0. N 10 r N It P4 f" 10 (v in ao N: ýý .0 e; ýo a 0. cv,
)1. 40 W%,tn 43-111% In -1 OD GD: co 0. W, w o W% :0 a -a; N F-;_ .' t - fft,in c'.4 UN 0 -1 Ijoft 110 fm 0 0 M .0"t m 0- 14*_%
10 w n .40
40 Q:'m 0 ca
I
W:dL
D 411;: LA 0. cl 1`41 c" gpý P-Na. P. act r:A& CKI ft ISO -4-N to r> In: C) t- 4P 10 N -t r1% co wi-o -4 a. CD
:9 0 a & 1 040 cv 40LU V%
4D 0 cl. 0 CIO '5
uj '401 f3l
CTJ4A wv
40m cm to U.,
:& .0 cola, Vý tim 41 Wo% 4-7 czio X; on tv _._'10 -rl
Cl >
au .4 r; .41 r;
In 0 V;1 f- In ýr on' .40 .0 -t 'o cp. r-ý T50 0 N 0'r- In .00. 1-. ry W% 0 01, lu IN P_ fý &10 01: WI P.,b: of a W% -cc N 0 A 0 r- 4 mma ?-. -.4 M ýN Q- UN, P- fsIt a 101ý0 IdIk
U. -1 .11 W% P_ N 0ý N OIL I"%?- F. I to m r 411111011% - Mjf W W% b4N GCW 4In 0 %ji .4 [A .4; - .0 col " - '..1I P4 - cc ;.m ! -`La C) N 0"1 N 0! -t 40 01 0 40 c
CID ý8
Jý 'o In N N1 '0 0 um N N N V%ýLn fý'm cc F, a., %A02 (1391 .4 f-+ w f- -I OD 'o in co '0 A; F-0 F-i ýa 10 41 -T
C; CP .1 . InUM .0 W%f.4' to f", N If" 04 ISO f" M Wto' N: a. fý N al No' rý " -9 - cpý
fm uj a% -4 -4 01- 4 In q'i W 0WO uiw m If% CO 4, 0 -ýr '0%ni" -, 1 N qm ()ý c In cý a 1'ý (). -Z' F-1 400(v '(qn"05 f" =0 en .' 0 "%1,; fn .4 g fn 0 rm .1 m *I en 14^ te 4ý N 4i %A 4ý' rý 't N eni Irý ry C-j t-4 ILU a
I. Ot de 0 a 0 i a 10uj-9 - F- ý a CIO 0 mjt wý o I- o' es co In, gN o !o I" u%; N= 4 'Vý 'IlZ I 'I t C3 cc 0, InH-i n 'n , ("i Iml cc WN co w .01 c' N'Oc of ;'L U." "1 11- J 01 P. It^ f"! 4 .0 r, on W (0*1.; c; .41
rn uj .4 - 'd3
1.0,11 101 cc 0-W I- J.- I in!
Hr-Afl k.,t NJ& 3694A-aoao L. I
- *
S* .i -• ,. , ,+ +9 -0 .i jr...'i 4+ no". ..%i
~ 0 .4. . !.. .,U+ .4,-. L.4*e.- 1
v% If fm ,S 1 A i s:' ok•J 4
,,*s>s: ,MO , * N 'In~~0~ P.~ f" :,- Nu,%
f .d,..P- -o40,. .,<1i.o N4O .0,0f1 .. J, t NOII *,m o-.f 0,4 q ,, N ,,.0I N , 0 C ' . N 0 4D¢ Al 'In P"i4 1 A 10 " 9 "9": P" - Ndf,- P.'U P. 4r', 1ý r- 1-ýp- III- P,- P- Wý P,,,
ic 4 t; ' ; ; 11 ',
4D ft. 'm. Or. P.) mJ 10VI 0 D i
W ~ ~ ~ 4 0'C4) is; z~' A*O NOO NOl C?'O Nti .A-N P01~
1.40t 4 m 1.4v .4*14 101;A.4 mAq N, 44% .N*44
ON N~' ~ ~ W 044% f% .4 PP. M..-+,I'41' ",, 0-
0(4 I+40' N o,-3" N oA N C = 01'• nl *P0-1• 4 .0" 01, ' 0
o .' . . . I , ,z I *
4r0 0. f% , - 0 , C. 1 .3
M0 am mo oo - r-,o 'noo ay # 0 e% 90 m r-0 a0 aP.D a D40.1 I* j0 #,- A.0 9 .t 1d .00 'No 1( 9 ' .0, 3I 01Qf. )0 W% .N .-0,
%' 10 ** I.n .- 0 ,0. *W ,.0 *4P ,0*4N * *t1 *,i , • ,.9 *90 ' ,40
C .+1 I• -'' + , .+ ' '
C' . 0 *o' . fl, N ,.'. IN .0 .0+ N , ,,.,,. .*.. 00 -,,,'< . -,00 4. , ,., MN.
8* a*~ 010 ~04 tto00 '30 C; 8 ,
0 I " " . . .I f a%04.o,,,t ,I It , I' -, V+,, I- 00,,,.-o,, ,IfI'0A '. ". ,, .0iea-
oor 1 : 0' ;O 0 0 ; *I
, . . a .. e . 0 . 0, l. - .So- , 0,
"-'m 9- N W 0 M' 0 P.4 "0 in ale s,' N'4 *' 9014 -inf *I m N IL * O In w Om In
09 4N 'CON if, 0 c' - 10 . ; -1 l #10 1 C.!0
a.0 CA0 00 00C 0000-,N - i 4P
L% y N el INI . 0 4In W, W `90U% 4P # W.'0.- t . 9 0 0;,, 01 410 N so N 0 04 0 0 M 1-4N, I, 4 e
( a I 00 "r'-
"C. .- .' 90 .0, .1., 0 0
'- a00 0 0 I P: F. in . o Ca N W% o n 0 1
o0 o, ., . ,0 *0 m ,P. In
0 0 0 0• 0 o 01 0 ; 0' no NS
O WI a, a W% 0 .
U •0o I*440,' 4* o'M *- % , A O*P,.. WM•- .4NP MW.',, I eo 00 •
-o0 1 . • .4 0 om*0 .0.4"fWI ,.ONW '.-,001 *&
'..o+ .40 .4 0010 . • '-0 -40 ..,ol oo ,+, ,4 01
WII W In IS 4 ,0 t 100 0134 g-, I,- N P Pq W,4-I ';*-"r4 4-'
. .0, N 4 0, , -1 C3 a AS ,~ * . F . . . .*4 69-0
J NMo ! i..4Mo
09 4.4 n f" *.4* 4 P-. w ,4-4 f" do 0 t 4- .f- * 0 007, .0 t.w w-o '. 4 .in0 a4 X4 -4 0 0 4y4 14o0t0 MW '0 F - N .4 01 11%% Nm aPt r - V- .4 .00
4A~ $t(4P 0. 40 4 .OM 44M A z4)-O f4-U .o I " fOW 1.4)) m 094
*NI.0N ? " 9 , -* ,-9 ,- 9- ... I-
.: 7 .i *.4 IP " * : INN, =P- o•"'i4 M- PIl Al 0 4 0= MA' MOl •I'- O "( 0 90 "N W.i ' 00•" 1 0(4ll WI- 4d1,ON
00 f;Ono f" C , o,4 - - -
N 61 4 W% P o 0 0 CID W 0 .0 in°
10. 890 0 1'( In+ ,- D f" :3 -:1
-. .4i,• .L4 .1: • -. N4 AV M-r% a W- ý0' 'm" - "to ,p- s o1-- " 0 0 ", 1 4, 4; 14 .- 49 4 Qj t-II L
, -- , q4 -I-..- Jý 11P..,~ ~ ~ ~ ~ ~ ~~~~~~~~~~C 0.,., I$,4oo:.,oo,,oo,,,o- ,ioo,.+-.,,.
IT-DlpDtN.369*'.A80oO -p Iage A-3
0~0
*QN.V~Cft rlQ4,Ap- m.0
.09 at10 irdIIVN0f'drVa.1 ;*1~ V 4E .1ý4if 0 0 a
*.0 to 1 4 * onr 0V.B.rýNP 0'.r 44
9L ez !, n 0lS W'. d Q - D . -.O
v 0 P-i.~ Of .0 4 0%tf c" '0a~ 1--
* .i 0.. ie 'a ' 0.* . (1'' C
0, cz Gz-co C. -'. '0" .3~d 1.
C; 11; 0O3'...' 13 4; '-4
0.t v doo -1
*j10O P4c'~ " 0 130 0 0 aIo c Or SagZ ,. 00no.
IA Z QQ 3' . 09ý00C V0nMC .C
4 4LLD
.4 .,% to * I" CO * 0 * V_ 4" * * * 10 1 *C ý 0ý.C
WNU Lu ** 2 r~O- . % cQ 4c flra 4
09 cc 0 1 03 1a r 71 Q0 CNO Z Zi~ .' C.
*I 9) 4o 0c 9tIS-14 -41 , 41
06 A-0..4 :4j..a ý--- 0
ADI COO.0'O0 .02 2 '. ;0I e% ** 41 ., !. t- m 'n*O .
.j LI I oiIA U4 "Usi l
!L. a %u m0 f't- N icy 4 't v (. 0ru P- .tV% -r Pa
O 1wy ' rI 0 A caMrS - 0- .40'o~ 4-a 0.0 0oo^'-900 nU- m0 ̂ j (ýE4 ( LaVfl % im V ~f~l 0F.-.4 4 I 4-to (7io&Mcc! ý i
C, 0 c0 Jcc c:nc a
0 fn 0'0no
CL 1.' m - ca 0ý Fo C al("~
.j S i
4R. V: ; Q ,m M*.. . . . . . *.. .
P. Best Aailable CopyIAD .
fm ON4W -P. ,0
MC-ADl £pp'rtNa. 369-A-8020W I.' d *s *j'l *t,44
I-S.W .. 6S0 Ni enF o n 4 11, 04 4DiA.4 'D i
.' 0 a 0 ,I*'0 NP*- l ll.NI ll 4 IA .r. ~ 0)f ,:1. a'~ Jug W W%*, *. .4 .r
'. ** IU tic 00 r.. .r I
.- o 4*e
w 4w .. c.'' IM- cc-.,~ III6 a.. AO N Oh 01,
0 A 'a 1 06... 4 .i~r .0 1 Lr " , 4 1'N j 0 10 'Il I In40 " .I *N~~~~ ~ 0 *0 N *IS. in. aN *N 4~ fV~ N
'f7' t- m I C) ~ 11N N0 in 4 oom n N in CF-
! INN C! '~~ ".0 U.ý S", . A 23 N n
I. iL *- M. I Vý to. 0N. 4'c 94t-c
e* 00 ci CN C3C
!in, Ic7 C%- Cs% no.~ ANI 9; 1 Q4,0111 we.
cc4' fqU .,0 *fi,. 4 N " I
in~. in 6'% W0 N~ 0IM' t .0. r* IF M a* P-0C L
aN Ng. 0(4g
.1 , nCp Ica It N It 40 'a -000 - 0 6p.%A
46 j ' * .11 , 1
~ ~g~ g i :. I I
N, 1 .N *O..a ,,4 0 A
u5 0 * . O~ f O O C CK 0a~4Nf N. C% N .I* * 4 I ~ .N *.' ~ i.3JI
W~~~ 0! *M *'** 10f *N IN* *~I *I 0A *j~2L 6 A0 0i
:OL -a I t Is d. a. *..
* ~ ~ ~ . P-4 pr- -Sm It to" ~ N -4 .CI .* 4C' .i.. m ' ~ N 9
"r U 111: V4.0'CO ONICC ONO4 0N4 .-a MNN IA,40 0 Co' .0 *4 0!II9 1&; l; ? *I g, LM , (3.=.~w ~ 3IA-4 0~ 1 C0 ell,.. 0.4.F S i0 ''c %' '4*
:C CV. 00 1 c0 4 ;2 ; . I
10 0 n n 'M 0 #is 5 & '
0I CC 0 0N,1 :0 .00 4
*0IA.- I'M SiN A IVII~ T* N (1 M l A4dV "4' Z4IV *1 NI N1 atIC S AMa*.V.j uA. -" ~ :1 45 .0. MC* .IAV.S I -! 0141 -IC 1
i P4 'r. IAN MIN i n V. 1, N . UiFN z .4'. ;A NN C- '02 .03 o
0 a a a ' 0 0
-1
Ir~~~i NnU.L In N C" N *0 ; . . . V ~ C N I O 'Nini I-e in, M in~ In.- M-- wii tn
g gi fe
d F
-1-6
411V- - F-- .
4 le" oI*P
Al . 4'* ct~.0t1?C
14i 0 Ný
*C c
LM m N w QNiq¶f- 0 tN0
PI I4 N~f -4 4.4 -4
II I?. II I I
Joe LA. 4Y 904NmP
_ ~ f trc No eac' MA W
M04 CI0 N3,r V
-J 1 Iu., O' ' 1) . 4 0
0 lul, lIII 0Q 0 4N P 14 1- Px 4IC% #' r-IlI 0 W 0031p 1V
m5 r' l CIS -ON 9- N4C, 03Ca fC. -
l 00 0 PI N P S . I. O *de t- 10 0:~ 00-an 0s -Lu a 14 4w a41 fII ~ON nf
w u 0 F3. 0 0;"n f0 m4!
A I- I
w .- 0 1
- N -. i e)I
tu.344tAu Ppge A 6
43~ OW mVM. C f" .4 1 4g. 4lf4 N M -Ip
-. -4m In "1 120 1ia a0 'e .0 ai onn an .a 4r ft
-'r' C2 p.a I@ In i n 0Pmme
1* 61, 4PPi I " f "I W .
0 i I 0 .4 0fVA ~~i 42 in; i.
-07 1.
M.WC mo 1.4i' 0- W.-d -4 lII ON,. (pa 0iI,:C4 t 400N a 0 L t3 O !
IWO It IC 0 q:3~ ~ ~~~c n o avu q4~ao
on~ * P. cu wt or tor f" WPa
4j .m2. .0 . R~ ~ ~
- ~ ~ ~ ~ ~ P WT , 0~m.P
oin 4a r'u IV ca C4
Ptt V
14 -4.. 4r er. -IV- 0r. .%-4 1 -M llsJ %n;: F~n Wt cc1 U .0
q J -* - IZC 4CD L~ C . U
In Il
W'i l.m ~~:4 4 I*I4 .r
US, - uv ci .4
In tj 1 ý , 4 " C7 tra. In I0
ccU L7 cc .L N v # 04'o IJN J . 4 U-43 :I- Ja N ri.O- '-
41
I;is Orm IDm 0 --I*?,gl usl *PP.; ý F" * T
-. vUi I. I*. * r
In - In (.4c
~r u c.r j ~,.;j4U e V i ":..~ -.. d m s r"j .- . 'N . le,
zc z d 04to* % 4 to.j 1 , IrI4 Is, W% *-t C.1 fM * L'S -~N4 -
IjJ N 'SP q N ,hl."jW
z :,p U %fN 0NLj Lj<
est "ala e co Y.' q
EC-Ab Repttrt N4 369 A-S020 Py. gt iJ7aoj
~jo 0 0
aft 0:: ::0 in. on~ 41 #ft :q r 1: a*~. -W- :0ý9- 4WP a ~ '. ma ~ a P1 Ft r~. . i .40! .
P.~F 0I@ 0, C, Pi ... - -*4 -d@ . 1U 4a0 ~4InP. F.PrVP - O P i. 1I0 P. 0 1
Pdf P4; C;P 4;~ 4; 0 C; *4F 4;!*; t 0 *P
a.4 Ie f" VINO inO in in 06i . n . r nftC 044 ?.U) 2W E 'n "' T'0 0 o pl voom @0 0 0 0D 0 0o 0 0, 0~ 45 A0 000 0j 4 : 1;zZ,
*~~ 00 0@~ 00 @0 I cm0
It~, ~ 0 f " P 0 P .W % t o m) @ 110 0 in 0 0. P W U ) 9 - ) . 4 4 2,
t. @j a a*: -I ~ Fum m0 t- 4r 1o 40 4n 1 0w oft C& ; o 1.90 rIP. A 0v ( n. 00 .4.PPrl9p . n W 4 0
'9-P N ft!; w 0. 094 ev g4 s-m *
. Q4W a' 0 ,
S *Po. cooN Z ill 11Af. %PPP t"4. VU
* 0 ft cm 0 411 0, II0 .4 a C 5 . I:
a1 ;co 0 * 0 00* 0 -EQ 4# .P' 0 14U tA-P INN C;. ,0 *- 0 C; 01 c ~
0 I 0.. .. Ow 0 n.4
4.1 * P. :40U *ul1' F- w w*. 0r " ClP *CW *.4 * - **UP.a*4 P. ( wO Bf-C a-LA 0B "1GJ tr a .Ar s %VIqU wIUL -ej tn fn W%~ co inGs~ wnr 1`4 .~
CV S.. -,4r C~C J, ~'1IIi 'm. cp W 10 9 In.~ r'- w .. T"C- I,4p( t..~ ~~. .4w - 's r ,on .W .& 44 Is
U% mn~j Is~r P- %n v- *Mill in5 -.4 Cl 44 - "44 onJ'O CP 'A 'r clU( -i 91; -a, ) Ul CU'ww?' U
o UlriC 545*. iiv 4.5* UlrIVw''d'."- '0s ' Pl*~ .4 P0 -rV c CDr4 - P-' d a4NiOt M uC,- s- I* Up- .CS I .5- b- _A f v_ Iwf me " 4 1 Q t
to tI 00IB III .'f fII M
-0, 44U co 4) 1 -n Cs 12. -TL 0 r iQ r. 0.-4'f. ". i n InII00 - I.
-~~~r ej = 4 -- "4 I'
C-bR tN 4 369-A-802OB 1?Ap.
a M I - b 0It.41 a.; ap m.; am .. a.e C. v~ 0
inP F .- p.W1P W ~ lo-rn eb1P - "0-. p-I a, an
P. ab I"0W0 'a ma 00~uaP a 0.; 00 0; oo lo a
pl'- rl U-o
t44 in*, I% t nI
0 ~ ~ : 6 .. 2i *
o P 04 1
000 t' ru.~ u ~ a a 0 0~ .v'0 U. U. .w I M'. 1w *j q7..
10 0 v 0c A-wý% wX n ~ o' %j %J as; 4'" *-* -
-In 0-px Zni %mw t r 0 .eI
'4 w tw inP 4 i v'~ *om *.o r.:'j `14 -40 1-~ lotNM 0 " on I-% In v
In 0* nI r. I " I ý r- mo u*, no n4 . w 44 '4v c
:. p a a0 0* r- o 0LIa 'P "a. .0 M w%j' I&
w4 r) -. W wl'4 I" vn i4 -J4 III cv 7
.-II 'J l'J.44 r-" I 4 Z
t. 0 *.
* ~ ~ .4 S II
I-I M. cc aD o E ' CI '4 M =I
cm . 4m .u 4 u% .w lu 4 W 43 -4 W 4%4rL -r -*¶ 4 j cy I;:'
'a In-' .4" 'r con I-% Ina
-0 em 4 u% In m NO I-- InI -a5 m4 U- ' -I o
-l - I c4 i .4 -. .-A -- r,. " ri 'j"a- Ne Ný a.-N 154 ftw .N' I'. 4. u.
IRC-AtiIlp rtc 369 A-SOZO. bestrduca
COPY 6
I@~ O o u1m@ ag .1 .j-- 9. 141-4Vl.
' '0q0q00 EaQOO 00000 @@paO
d; 1 m 4; c.0 4 .d# W;~V 4; ; ;; ; 0 00 00 o 00
11- IV 08 .11, 0%0 00 Ito
4J in i aM-. o b30 Ibaiz U00I.D0" a0 oD .DW pt)L
VI1% IS? V411'.4lgtC In"iae e -r-cv =4 Om:r. z
o * 00 1* 0 * 0 a * *0 a" S*0 9 a
kp f- in w 0 - Q M w f .
SW 9 "~~~0' .0 w z " ^ 41 a
43 .4o ni.r4, - r.0 4 . wI
I .jnpj 'A~ I g" ,.:
q.% I v1 11 9 M go360. "' IO"&no9v"J' U I.f
5aUn 1J?.rt * 0,U"
%j C% V
u~~~s. Cs " I , Go S e
-VC on 1* I vft eWk W :1 ý Wlr ISO-.. en J F"' I!!C4P4 n
bes SI d av; (ror
1e IN*WV. vibe m*4 lIWOI 0 COPY. aI
in 6. 10 In
-nu i. It
'00 4; 49 0 0.@ w a0 'n w- ~a~~0 asa*. o ~ .ea *~ .u- ~ *
V4 * 0 . t" .N W'04 11au .
CX.in.0 fy Na 'm' -W on~' .fin Of"P . c
Li I so .* J
OI w 1 C~. .- a .e *a ee a on
.4 .. -W7.W In07N 77:*j 4 ! *J *Ir .;1! -N
PC d WJ' a ry -- * 4w a oro .0 74.4 m .1 .&a - M e.!. a - cp'- ,'r r4t V WQ
1. 0
Z' ai 0M ' n
-J in. 7nm - .~ kp i 40 C inf' fr I V P..16 w %,,-o I I j q.-
1; 6- 1-1 Va9 A .-
*1r' 4; to4 * ' ; Ice .-
l. A 0. 1.-. C ~ . ' .~' .1~ iA4f 0z 1 4W 0P %W oC 4
4I . i
.j W.O ' .I ;!9. -7 *ý. --1 * Q) w. r" I M . IvIz 'J. -~ 4G'.Wt ots 4p Ui7 Wl'. PI*. u'gm CN -0
I., W 4 " .
-- UL1 4* cp r: I" * 4 I
-> I
v. in wqIP% Cav r- V CO - ,I 0 "Vbr
U, Q..U C'*.2
*
in-L QU
UJf1 . in r.2 In -l 0
U a I- on -ri cm -I aAli' cc~ V, C
e-. I av C0 %o "
ET.C-Aj$R. prtNq. 369 A-SOZO ijag* A-1
I VI* t Ste 9 040 IO
W1'0 . P- *4Q 0. .tP: 4. m
IZot f" in 4. 4.
1; w0 I@ 0 00%'O i0.O@ @0. 0 0 @
I'or 4N N 40 -- ft,4 4 0 44 w41 4 0 in. 4 4 .
a~: a @c5 V 1 @ .00 a or 40 W
0J004 '0000 @ *0 0 0
0 yo -0 n r I:00M0a i: 4W cc~ -; 1~ 40".014 *01 on wob .0-40 *1V *Wf g','
in o r cp inU IV ft46 r.4 4W In rw-01 P, c--4 "%If~ r
4 ' 0440, P. P. e r. FSNU W 01 44w -74. = r- 4 " I=O 4
1 3 lJ0 0o w mat' 3 ,
IV 9l. on to. .:.d in w i ; I
0 '0 00: 10 0 '
c .9414 @14 @1600 43 ow- c4 *00 04P op
*of 0 d 0 . 0: f. 0
I- I 4pI
I 3- .ýn 1%p1 . % rq0r ON 1 CM 1 .0 Ls 9% .I .-6 Co
p t 4U4' 4; 10 go .40 LN 1% 01 j6.I
C'." W', fir f. C ' tI A m w .
9.C 9% r. 9 9 93
*~~~~~~~~i 0 00 ' "~0 - c 0 IIa*I I, , tj a 4 I4In m 1. @ vf c4% r. 54p Its NA P- I4 *44L.*~ 9%N 9.
.0 %r "In Jop gý I vr P"*
*04 *%~ .10% 44 ;f4
.-- r
qp 'r IV; . ~.
.4~~~~a c p -1' -e.~ i M %I ~ 1 5 1 0 -o i n S47 -0~l . '1. C05 4 4 .. q 4( %n N
4 2 W490 a 40. w a. - P, 941 -4.4 0 *ý0 I4 *-n 4 1 "" 1- f-I
I I u
D l 410-3 P1'4,naf- k 0%LpIN -I0%e ,P -r .P'-'-5n a N0P C56. NUL
0~ ~ .. 7 46? 4 4 - 94 :5. L6.. , O l,) 4 .1 .0 9 0 **J IS 95091. 94
N~~ ~ r446 V46 .476 f-16 46 00 *- (
*% 4.4 LI r. * .
I V W - s V %US ~ ~ ~ ~ c Q4 41' 4.N 4044 WI 4 51.3 6PJ 4 p00 .6 % W 4 IN 0 I 54
.4.- C.A~a ley " XL 36 A-80t li J -12.AI
4~ 00 4. 4
S . i a ow -' .0 to C4 ~ , 4~ m1"*~ a -. 4% P .@0 0 1
4; * 1. 00 00- 0 .
-me .04.0 . 1.m 0 in~~ ~ -dmm *mt .0 P1 mm Z4 104 Irl OR1w: :0 I g:a 0 go0:nC. a 00 C 1o a o1 @0 o 00. 1 2 w 0 C; 4
IId Io 9.O-, W
MV. ft " am .4. 4 ON W' . FP.. NW N . 49"It 0"
;V -- ': @@ . 1
,.D a C,~ 0 J 'JO 40 0 . 0 40
*N fob. * *00 rP W *- m * ~
~~@-' ;; *O 0. .c ~ 4 o- . -- 40P -~ .'I0 *C w1 *0" env =0 *0 0 0 *@ * .0 *00~~~ 0 0U a a C' 0 0 0 0. 0 0
ol a a, a N J g o 0 L
aW.,r.* P. 0~ lp ONl *4D lum W p qN9 Offe %P%
04 a 0 -4 It 4
pf. on i W~ on 14 4D in 0a IV = .. I A . .04
*e, 40l 4%4m ini .40 INN !We . m .op ~~~~ ~ ~ .1 N"11PI0A n:P.
no .0 10, ~ 1: Ao C: _
*4 C. ý 0" P" 4 - 0
* o II1I, t3V,~ on~ *.i, m_0c1
.11 CW ; C I; *O" *. C;I.% .0
.0. I cu. N 0.0 -
If *0 PO a. - N %n 4 % J %.
Oun V. 00 U. 4j.. *Up. 4j V, t4*r oJ .. e .
*51 t 1 10 4m. *1 P% II, in F. a I-(r
fg%~~ -0kI0 nII -mW. 'nt 4% % p 4i rV4 P.im ui " dU U.%P .u W%0uW% a, a
u-% .. 4 'r C AD '-1~ .0VN .4 I4n I4n :- 4N In4Pam 7-4-4; ,I
-." I'M .
..I~ .1, .0 %jo *.1
LP4j1 %p-oS m11*.-~*g 11 I S- S 1 I 1 11 I'~ I -M *'I-
C-AD Is tA 39A.81 .eA1
9 ow
* IF
Ma r' ovwF
* .0
fttP 0 tE * ~ -a l 4 4W a~~*
Cj -Wi-0 0- - ,t
I~" A' I"110; w a~@ MW 6 a .10 xIv
it 't It CILW4 v I- N06 WO WGO 0- eI I" 4p
11.0 X. , ip WU%ý vj~ nn m
¶6r 0 a u
P%.tfF 0 t) 1; 4N.. 0.4 0 L. 04*PaP * u .1 r
eC' a CID 00 CP% fS0~ 40 00 Ot; PC
01 ol wlnr .. tum v ip.6.W;f.P1 -- .0 ft"M~ V.N 0k I~~u
04 a I
wv-n vi 0; ae- -y
ta N-v Iec on I - I in
Zip ) f -'P. P. .f
I 1 S 0.4 . -U. %A CA I
r i .0
-- -T tr -0 - - -
wr-o -to so - I.- -V ",ff - i
I* to-D 1: 1i2 00 1ý OT4 .t
C -A D o)tN 6 -00g A-14
betavailablerm
1NN eedN ~~~~.I N4. aPIIN4 ftN" NNN
!.4 j j; ;; 0c00 4;cl aoaoa;ua aaa aoo 0 0000 0 C i 0 0 C2
M ~ ~ ~~~%fa 0t~ a.-,0,0 y , 4 .04.f 0 p(,c, 0a . WL oQ
ff ;qi U 44l a, a, 'i4 a- a- : V. M a.Ipv M a- 0000 o Oc Ooao0 OVA oa-o- cr o- 00ao- 7v"c% c
I ~~~"r '00wm MM""N~,~o~o0a N1 ,0 ftc'~a C40
''
, , p 10%, -dOfe QVE, too
10 Z I A.. ".wgnnI"
M 4 0 F- -, 0 in4~.D 00 au 8I0.X)0CP 9% ~rowf M P. M P00
42 rM~ oý ' AL.%ue -I NMP Vel 0- m.0 .F r W W "rr0f ý-,o egfUlow
-~ ~~~~~~W m~ agc.-fra oio o' ,oo0 4 LI41W W q00 rLI In~r~ t~i a e in LO~0
EJ4%w ~40..V: in 0 NN4 E' P .04 in a t r- 1 NiIII4 1 w w ww - in4 -;; W =~w -. l4 i4p. Nf , Owl M MM. ."Wm Wi r4 MN0"'0
O ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ý UIa 9 EIN l4*ý .l0INPmp -0 W UI 4 Wqif' ~ ~ ~ ~ ~ ~ ~ F CA on' WIC) IF%100 wL u%~l 040o %nll0~'q0 1.0L"IM* cm M N.0-"naM g~wia " -M M -M M..0t m.''J'-I
-~C rQoOC.*. no
0~ 0.01
-* Ip -, .: m fu - ca t. wwo in .4o .0u'.4 In ~o C ;e w.!9 OW i -Lo o t~t r- M% il.
1-I . ~ N g. ...- 4 ' fý'I
MI %AC) rW m -1% nV
-K0 U4On - CA W" w U. %P lAd- ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ (I N 10) -r -7. f"'N 0't 'r iN. .- y r, I":f f ( D0 ~bIIVII1 ,Q ed ~ - I : -,
W 2- f4 CY w r- w Ar- w% a r %n 43, in in0. f.11- N. 41 .. N1 DO.%;pc J u )ýP %o -,bu u - I...
CA 1' ;4 .. . ~ -.1 % 1 0 .C' . 40 . -. .~ 0 L. C fjcp rc 4 ;c . ;q
w .P, F-7 0,4 a- 4 a. V* a.ý ei -.. rg.- - --. *I--4~- - W -4 a-A- - ---- I1
3U 1 89 1 0 c &J4404
*V V . .I .' :1. O.0
P. ID oft ID' (V 4'J 41 UJ 'U 4) --- CU rD ý mf ft 0. - a4 -A d - 4 W- 9 Q. .P P- -IK -p -0 -, CA44 W. V4P c r . r - - -r ; -?.
- ~ ~ : 0. .4. . .4- .N . . . . . 0 "41 4Sd 'SJ 1; I I~'I I IIAr f. e n*f --m4
EC-AD R.prt No. 369;AI-8O20
I ma O@@D 'D ro00 000 ON& A~ am o
4,Cr fq In .064 4~ -0F. 'r WN ft l'N
P. i- %nj Fr* -' on- vE~ F' o
sow C;I ijz !0 mA0 'j
IM W
-.004~ .i a j0i0Or i 4 aX 4p - in N C' P 4W 4
C; C; C7 * : 0 ,9
Wdqj CID .0,I~ ..ý i WJnu .o.. *r- W ~ p Alio *Dm :W l
W 6 uC.W WW .7 W * I an -.A)C I- d- a- %Wihv 'r " 41 : " It 'r r1'. 61 -.3 at 0- l 'l
-: *IU" 9* C:(
03 0. to. I% 0 ' ~ 3
F.. 46. ý v. .;
: 12 : ! 'p-0 L
Pj'J 0l -f Ir 0' fn". ~ - C P'." *
o- 4W C.A ix 121 2% 7.V 7 M41vW %ol nIll % Q' *:.- **'t' W -- A ".. 'Lo .4 r4. W~F IL.. *.
N II""I U~'"~ o"I C;.' _41 .'J . 4r- 1oI U'I
.flLU ft 1" .P -. U ob m i" v' * S
N Li' ~'*' - -s *
cx Co
a, I - £4 IICl ~ U '4I .~bl~ .I 1UF nbl ~ ''
I C-Aba Rej 439 -0a ~ ~ ~ g A. * 1l6
4.41 4- ' p. * 4.
=4 *,. P-O. .4.0in . In of P- a. t-4 a 44 a 4D r-
" a Zap- a.- an a 0-~ w a P- *e- utdee
00 4;j 0 q *
4p : *,mP. 4p -r v 14 P' 0 4 " 0 v4.14p -I ~e *Wobl a 4F& n 0, It
ii-v'~ 111q 4: '40 C* v lop 4AI @D Z C,0 P-V .4 ft "IM, f4o,v, ai o m 1 o 4 ev 4on, -C4 f" W= wN w W. -r w1 a4 w lea
!0;.4,V~a 0 "0I I sI0. :80 '00 a 00 00
P. Me-.4 c. '1e 4 w 4 p alP- Oc0N w 4 0U'-t -PI N "I 4
,iN ~ oV: .1. !;5 In-P 1;~05 *4 M' W4 w 5
Vl.p. O w #4 in .4et 0 ' A~ .P.f .i 'aa @O loP,~ Q 00 0w IW W '00
a0 00 9x0 0 UC3 03
le -W oi :va qr " 04 0 0 IN 4D In a f ; %j I
*q0 .4,0 ".., EoUW '04 N4 'Da p ~IV p- 9 a aw IV 0 in solo* ~ I
P.%UN ?06. 0. .4 0 m u 9 *' a 004 -r UP .4133 WQ w
1,3 00~ 0 ;09 0 0 9 0 jo 0 ca u0 0
@40I6 I f9- on- 0 Ast- *0'9-- 00' 2 0 * v -9Pq 04.40 t-.a o06
0 0
PIZ~4 *Pt' wo0 @06 IA *0. 0 -l *Pp C%- 0 -x6 42~ * 06
4r C N qn06 040,40 0.a4 'P. 11 P. a m4( ft 6 w WPW -0' 4 0 6IM C060ak w. 0 aW% 4pinZ -,P I4.09 0% .4 'a ý Ot I- In ILI4 W%. r.
.0. ,. :'jr oc o t t ,.0,f In "* v a -a 0ý w ~ inj v ao r r a4P
oP" .- 4 .D 0 4 fV4 M4 *4:61 -6 f2 .U j
r0p 110 0r 0 P
4:f-; IMO60 oft6 -re .0 I- gN-e .4 rr., I" - P*.4 I" r- Io- A r-6 *Af1.4 n i -o 0o'P "I
C. 4 M 14004 M rd4 1If 44P %S 4P.p 1
*4 , '0 0 0 0.0In o CN on ft 4p: in I , IP. 4*'N Co.0 =.9 w9- la't w~. -910 w d - p- .4 t6. .04 P_, 9.e
06 *t 404 4*~E .0cr.0- .. ~6 . .06p 400 -4~4 V .404 1* NI' ~ ~ ~ ~ ~ ~ ~ ~ l 4.0 C -.P
5.( ~ i 10 9 -c J .
a. in~. 42 . P Zf 4P P' '04. on 40 ic 4 D~ 9-0* 9-r ¶'r .0t. jp- 00 'v,, PW * 6 **1 0 . .% '0 ka UP OD f4 *I 0 .-0 1:: V. 9- .F
on '' P-1N* 01 * fl.t. 69.). v... ~...* V.. 0~ ~.46.0 ie. t. 4..N!
In-.I V,. . 4.Wl 4.%nt
1" I'MII IV C
6 *0 00 t- 4 400 w9 In0
-v 09... 111101 cu f'. CD P9-. Wu..- WP.. cu r- -T toI- c - C'
.4 6.0 S * t. 54 I5. 11 46 0 6. t-0 *ý on. t - 1
~jrodu~~'.,..
est ed %0 vo %
%00 a~ 4a r 0
IVcm# .0# In 1 04 004
_0 I ,.P li n4 '
,..* A4 .0n m ~ . 440 aW IP4 4
'.a s : : As , 2. I. e w Oe" .00 0 O 0 in .4 f0 0Q00. 0
.01 q0 I* a 0 C 0 100
@0~ au 0 00t~ 0Do rC; 4; C;C; J 00 00 0~ 0 0 0~ @
04 .;*4 491 twin *0! Ni IP 490W- - *1. 0:1- Ow04 m P.
0. 4 41. 04' bi cm' 0mw 10 144 ... Ba . t4 040
coo 00 %P 00 00 qw4 00 0 0j
SO~~~Pm co40 t 4 0 IO 9
- 0(S 11*. 0* a 0.4 0. C31a 0 C; 00r
4..4.4 944 .. a mm -ml ar*fl'4. -. -' :Q ;,n ;; .. 0
0f 1) 1 c
-;e .o I ;9~.000 0 in w4AP
in4 in -cm 40 on4 4.%P V" MaNN I. .m Mai4* 1440
.0 ft' C, in 4 e j FOS .0C''4 C . 0Q di .43 -M4 - 14 " I- .~ 4
m1 4p X i 0 M:: A O P * 0 Ir
"lC ! P0p4rn~ . .P Pf't 4. o0 44
ew 4p P wJ4 P-414 -441 NW. 044 00 ~ .4 4 '
w11N 44 If -41d 0 40 U.4 La W. I F" ft 494'4 4- 4 Z.00 P4%
.1 C4 19 I.91 z f I . .n
w jj-aIS
~~rr-WJ 4C 4 - .
W-w :1 .9 -~ M .-S ml t, - - 4l -
r .40 . r . 4
'ON -' (P"'- U49 oat4 'Vs ~ .~1ý LF 0 srd P4 P-',
LP %p lu LP in"S AIVI) iS4 0 *0 90 0'*(.-T 4 Ar 4- - 4 . , 9 .
*e in fn inS-u fn91
fn 49.4 I=E~ 4~1f 4 ~ -C ~~ '.
- ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ L I .Q *4.4. .. 9 .. 0 4. .j.- 141 4.4 4 - U.1'44t-a rN r
99V 0r *ý N' 'n' c
Z' Z 1 r J44 .0 ~ 3.4,f rA9 **r'9 r4 '
*9n9 r-N~ *,IO '574 .44 ..-
coU v%.t .0
0J 4 ~ J 9 4I-4 4' ~ 41 1C 9 O 1 0 f,
LP to.. 44 wI 'A I .3 w 3.V 4L) In . II ; wl I I 9.-
r4 ev I I I
:14s
as 00 go 4 j. '00 0 ~0
.940
IN ., w m
TZ S
I. I
"*.4Ic . A , 0.' O 14 0, cug. QA ~ ~ ~ ~ ~ % lit mlU4 Q f"!.A *I~s ~ 4fm I-: i- *vp 4~~ q wI(..4 p4IAN mP * 9.IV W
WP.E ~ ~ ~ ~ ~ ~ ~~~~1 'W~4.IW *rj P ~ AAP4 .41 'N 09
In Rim 44j ft ow
q- C4 ,9 trw gs Y4 M
0 4 -'t4r 9 I4 *W D t'%.f 9U 4) rC4 .dt 1 0 rig P-- .494 W4 - U~~'d 't'W460.,44
:.qm 49 4'. M'tW.I *(w 4 9 M k '
*QI ~ ~ ~ ~ ~ ~ ~ & *'4r 4'- *U Q N m~9N .. -4 'I'I
a..
It co ' I +~
4 a . I-J Q4 4 4
w C, 0, r- 0. P- LP 4 rcc " n e at,4 .
Aj ~ ~ ~ * tj U jT2 40 4
mm* 1- ft'' -
o9wf1 0 .1 r*4.f v% y !n NIP 0 f N lU '4 D
IV% "I M: ~ f 6%. In ~ 41
W, . .% . .t
t** J. to no u, ,- 5
I4 *' 5,l"
'to o..- 41 4J6 *,I. .r .o 4. 44'
rn'r. 6 ~ 99 ~ ~ 1 4 i~~i 1. ~ 4 # 9-5-
* ~ r cm4 N S * '*S *; 4 9 S
"0.4) 4
IN,
.416 .4 ~ P ' 0 4-' 4 ' 9 344 u4
m C- )P"It-NO 369-A-8020 t .
FbesiC-available copy.
' 1 00 In IN
It. .W I'. :. P.. P.I
in 00 000ao@0000 00(0 a 00 Z0 0
*4 30L c;n4 00 4 *~N? 55N ~ 4 N
opi~~~~ ~~ 4p~d Iolafl4. a? 1~.V
N" '~
i-6
.V04 4060 p. ; "f~ aI WW o-. 0 P.P
4~00 10csD 00(~0
P.~~o u1 0o 0 Jrlan
C~ ~o or~0 O 41, .4r "0' i H IM I~ 04a Z cr.t co 10"0"
141~~~14 0- 440r CC~-. .. ~0 C3
M ' 0 F4 W4 QN ,
9v a 04"~ v fill0 0'' )l. Wg i"c-m *0 9A a. 4! a. WO UW .W *
E lie a C4 C;C 4; r 1; 1 0 ac D0 j4 8
-6fti MN Ino W~ .111,~ "1 00 Arm 0 ,00 M "I
P. (p V a, on P5 0
94 MU 01 UE aa1 VI '1 0, W ti o
lot -1l000 0 0 0 . *44 4 a IDzoa0 ,;f;' c;
P" ~P. 1 0
:Vc
C. nAf4 1,.A4dJ~rc 1c0 4.L 0(-' a c, r Zp 4; C; co1
iii ~ - f55 8 5 S -s oll r11 Will 1 .1 5In
us-O NPPE~ M. PlMV"on z .W
>.JJ . 5 0 *'~
40.1 xI mli, 1;5..;131,1 1 .5 5 c; c; #10-0- 1 6
""i il J-1 ý 4
r# 10 -A -j -j r. -
ISw lp tL 0 e C R l
P.I M n 4, O PA -1 i Pi
n .. . . . .. . . . . . .. . . . . . . . . . .
P. I O . ~ P 't " ~ ~ a
:,.A8O O -I•
4* +' i:TCZ p• eP' • % l N lo *I o , I -., . ,jo . S,
N ,,o-o -
+: • II .J "1 ( (++ ( ( o_'- '' - --" , - .- 4J l- z -- +• •+_ i+, i -. -il I
-' P ]I m p ' Cl + "' ,. ; u UJe dill IO ,I
S• ' :A, 5 • A
96.4. C ke , ., - *4 4*
A,* ow* 4w .0 ge ' n . tZ _MI. #0 a %M:00! ! 0
". : q (P I I S• d u+.= p,.+ , p. - • - +.+ eI-.'rJ '+. * . NU+.+ + .
G. M,~ .44N N ON0 (N I.0 4r r in
::' ,+. , II.•.l u ", N alU'O oo, P4U m tN4 'N- .i M- I+N4' -" . m* , + ..ri ,J , ~ .... ,.+ ;+e. ., u Iu0 CW 0 tj 0 w
. ' -I 0 + ., UJ *4. CI~ C" O *. O. " ~'m L •" a . *. I I U , , U
. . .5 i • "II NIo o -a~~~~f M.4.•I flt +1" 0,. , W-4n • +- ., UN+_ f+ ,- a ., -+- i+, in .
i00 'n %. .No F.
. +Op
OVI,-s. .w.i.e , , 4 3 *5 ,C )4 .C *
- +,g . , • , i- uc I D'7I0' : + '+ " " + 3+- '' " • _q + '''q .~ ,, .,, .^, C'• ri'" .,,,C
C"INYt<"?i " 7J LN CO 1 w O , C ,, NC *C'5 . 4 - *Uo *N,: ',
-4.4 .41. %4:Am P;4, '+eem *,.> .o'. ,•+ N.+- ,EOS ,.,4. 4.. . , U..o 4 '.in.,
08 'Ar-. 4.-4 COV'. ,.. i-O .'. '3 .43 *.Cq UC I •q Nu .-o sits, NO. , 1
*~1 C: CC
'0, ' WA V le" Q 0 -', ,. , :n V,..-+ N,,n
Ui
5 I l k • , ti f~4 4.m.C W .4ro' 4. .+ -2 in_" N'L., *I'I.4 WIVa - ellll'sn t m',-Ii -C ,4.*.-J),"jll
P.2 4 '. 0U'
:; i, . i ~ • w - ..•. - I- ... _5 . .. 4, a .1"... . ,C. r s. i,• *r• . 5," ,?" .., t. " '
is Z. in
F' } : , . 'il ' "~% ... l j+ "+ '1 " *'- " L " 'l - + -4I• 454. ,ci • 7 ? ,- ,, *.
t!.JCX .o) * 4 e..C- . .u u %.01'. UJ-4N..41I• m a ON ' aN - r .1 0, g AA o
Ki 4 M IN, . 5 k15,)' 'No 4 L' - "F
le ., N3 a in g .
Ft .. fa+-0~' L n SLlU1J C ~ '~4~ '*.i ' ?
I 43 ~ ~ ' I - ,4 I ~ ~.
Ve IA~ cell. r4 '4? or,. 4. '") (J ~ ~ 4'gl
4-. -el r' V%.. IF- '- . Neu "N -cufC~ N . .ell O N CW4. C N* fN. wC' 06C* . 'C ~ *
FIJFell Lm N-t In e. r -v ' WeN" fe,. in fI' "f n sN -el e. r: to"I4
• rjg. I . . I .. .I ''. 4 04...
~~f n -- '4 "1 e,-1 4
tu .4 it, Ni u a-
HC..AZ Ito, rt No. 36b9-k8020 so~gA.Z
- 40Q~ W 4: 0OEU-~t F- r- dp-
ýa usem* 006JLaqaaa
00
w w ,06 1 4* t-'
o ., . I,
a . 0N.44.Jf 000 fac
a. ~jtj z~r r j
f. w .- r- In In w
in ~ ~ ~ 60 aaa p--,us a -M40 0 cy w 0 (
p 't 4 % mc PftI'd44a .*0 O Ip p L p a@ T - -
4.Lie41.fr4
W4~ ~~~~ In2 I o -'e*yjw .9! ; = 7% A 11 z IW4 tft
cl Im )0. 'mf4-I U4'.Nm; r- s f4.n
nit!4.. 09 -<72 N~ftn 0"1F3 4)I' F l. . 4 .t2 % 4 : P '0 ~.
IL l 41 1V 9 - C0.4D 9J tOI CS404
4.3 , - X2IL - e
4%. P4 r 0 4
I0ý' 4
InZt0 - P rf
- C o
Reproduced from%W P bsi availabl COY
HI-AD Repqirt No.. 369.F-BOZQ2 n Pgo AZ22
41 W .0 *1
1:0 at 0.4 0,.0 O n I % 0 0,4 0 000.4 a-so P4 C M I'jIA IL N. 4~ 04 a C -4 A ft A
IL4. ""N W9. 44P PON .. z0-4 -
a 41 M0 i A 0 21
0 .?d. mo% N 70. a P r oI
01.0% CP 0% in.0or-.' 0 V 0.
U 0' i.' CA '00 *.0 1.O! aql .0400 0 * .I 010; .4lN 0 t..0 04~Q Cap 4 *I; N P .4; N; Q
FSW N NNa , t-lt4 P-A~ F2 arMam inO P-N 0U 'D i-: Ih. IL 44' -401C I 0 I;
.@0 * 42 ýw 0 T2 16: .IOU "
M in* 1- 0V , 4 D4
a. P10 IN :1IN 41 .0 C4 O. C J f) ý4 -11 a' 11P i 11 L
lUt .. l4 CL ~ a .
Ca .) (I Q '"N% 4dt W aN- IF11 M*t1- 1 .0 0 0 , Z fnc, ft.-
-L ..W N A .% U 'a4U%' MA -W f"QV '0 1'. P0- I &%CU In l)-44X -k L %,P4. -1 0,IUNrl In I% ILMI
1.14 46J wQ V0 . ;-I %a16a -4r 4JEO CS C:1 80 C1, o ' t
flU -A.6
ja- 4. Fg. ýO u0 w ow U'u Q cc *V 4, f4. .A N ' 114 I'C C
'0t. *, ** I.Oin .1#4U 41 U% I
V I*S ~
J; ~ ~ s-r' - I'jr In. .. J-
r- g. l 1 0CY n C
%J " 4N W4 .I 'U'C 0C.' W'CI 'll 41NIflU 4* w ',.* ! U U 'U 9 4J' ' I' 0 E4.* N '
136 I -i
*1u. Q. tj O.4q f" 0) 1 -10 -r I *''D r4 . L ~) 1 4 ) n
- ~ ~ ~ ~ ~ ~ 7 -IL .. i )4) 3)t nN. 1n 43~W In1 go .~J 'D ~ .4 IN
t- C) -n in !D q '-4 in V n"'=W,% o4ICyS- Q 3e! -' N , 411 0 '0
IRe prodeI~ * - best VavalabI~ronl 77h
W. 1C. A1 Reca No., 369- -SOZ6 Icop~y. P go A123
U 4 ' '0 4U. p .00 'a ~ a 1
M.0 NP- ! 040'a~ ai ea oo! 0?4 0 aP 'ONi~v 0 "
'up0 '0 0 a.00 UP .4410 .4- 9 4 WIW 1 4w.o .*i a. ft8 0 0 0_ 00 r0 00M0 N mm-Oj. d,& o 0*M N .An.ýI onO 11 O a 100 N
:00 4 C9- 41 ,a4; 044 7,;4 .4N C; #.O E0 0 d
in0 O 0p1 0. N4 Aý ftC~ 'V" NI '0w- W% @4 40 N 10 M 6
@0 0 0 00 W I~ F 'Q C 0 0 o9 in or
I O p ~ ~ *ri *4c *-.4 a.4 0.0 *.M N '0 * ý. A
30.4 on 1704~- v -.- -a -0 a .. t
00~' c! Q-000vC 00 Do .0 0 ' 0 O C
'0N r4 *. - ~ -0iP en(~ *'.P 0.A. UN *-O 0. 4
'. a i-n i Nc .411 I-'r4J 4n0 A6in~ in0 Z I rM , M~ :11 0 1 1Pr ' rt.tld - W 4C0 , * [4.* .4 " -t OW;- ý -11A' 13' l ~. 4. .4-M in
*0 .1 0 Q0 '3! CC, 0 "1 -11 .0 * 00 . 101 610 --
q;P. CJ0 U0 0; W0 4: `3 a 14%P Ic IM U.U a mc. Pc'co 4 ~ 4! 1 I in LP c 0 %Tai
co I Iy
r- 0 CD 4 %. .4'C i If,44 410-F- ( ii' I nWý o r 40 lcý P. IL"Ift 0" o. iCn, i a,0 -ir m1. - o C .Am co IVg c,.
W% UN -0 N a' 4 M!I.. in n Q' W1 ~In In Af% cW n Wln'JQ .1) A'Jn -'C4 0 N *
C; 00 0009 0C. 04, ~0 0043 00 -UP 0 *1 .: cb 0 c 0
mii P.' GI nC4(0I f)W'0. l* f- 4lr g4 WJN ino -ii4 .0.0 P- F- nI.nO 1 i 0 .. wl 4 P1 tp. In. M .i -4 'CD; U.aW M ' W~It I4D C* W. '47,CP431 0 CMOi 60-0- t LPC n I a -ii WU to1. 40 W41 WNW '0- ILP
fm11 a:- 'C0. Anl. fmO N.C'~ N' t-. 744 n-t) in'
0 fa C7 Oc1
:. v ý*r -rip
* 101! 1440 4.4 C-nt An0 MJ Co'I -4A 1-A) 4Pr P) F..P
U,4 All1 .44 W I P- TV .4 N4 p. - tP.4 u%1 .Oýn 4W~ %U %-I ' $. C% "11 'AC. *WA 0' N 40 I m 4.# 4v alo 00 ON 64 -4 F .4ainI if'sI.- "1 1- AC3- A1 064 A co I 1j:
C *1 C. tA 41 CII , I i ' "
CN I vi 0' (M 4,0 A44 P1 nn r4 Q7I-' 04 M )4 O 'L.ND 'ri 0.. o on c 4'& 1 q(
CIO 'Jo 0 . -CI0
I j 0 ;U : o
inco CUW%- in (p. m O:' P4Y -e r, I ellf 4' 45 m A-. -A in. %Ml '4 co ' .. N . 0- '0 1 4''
co0 -~4 -co 4, N*W -10 50` N45 in r-11 .'4 115c.0' cy
-01 "P I .. (014 01'l' Ia.4A m~'' in- Nr.. f,1J 11 cow m ofl r
An0 ". 1'! N cw a t - 0..0 04 ;( -TC% Iý4U' zN 'rI~ 40' CDO Cr lf* NO' N'n " j
wS U' , ti-1 CU(.- "1cp qa -0 ( Va VL
LP . 4AI L" V1 W I V (P5) (f. ,a ,%Cu L"U An t- ill tN U', M P4 111 % L" 1- W% 'Sl-i Pin.. k^', c- -In Au 'D 'Ii *fl 5 0 ' L n f- 'fs .1 ;t- - .1
. r '3 1:- .14. i '0 a 4 A 0Im I'to -w 0 "1ID*0 1 It ;ZA V11 W
4-C 9; 01 .: ' Z44 4. 4'4- f" -TO LJ4 e4 I -.
0, in 4O CA ' 5 0. 0
tAGa NI 6 A..3fli 2 ~gA44
In, ingo s -4r wwv 1 4 V% 1Uf
aw4a',f cao me 0 ft Mi am mr.i a
*VM*-. O.JS- 0. V*: w 4 **r
in C. ; w , F 00;P.C P.; O
id ~ ~ ~ ~ C C0 M6Id N 0~ WU- t4
'i - .hIft M.4 f . . WU A 'd F- C-4
' 0 . 0 M V 3 0 0. d - 0 T - in ~tv a-I - - 0Pd t1
tj a rm co AB
0 a cao 4p W,
,4 L - f 4. n40.9 tj 01t 4 WC :4, z
0JS a 92 m l *fi 03 'Co0
In-a xy z.~~ :e '-P 4' -or QU-MQ-q lin v~'U 6 -r v W w%~. or 4~ w
in ¶@ 1.2 tv Ziaf *q ,411 un 1 WO I.". 1 i
to ai a; rc 0
f onPI V .1-i4 fn M .14 - NPCl *g% .'I C Cl
COf u m
rlv 4. 06''4' 0t ion' IL~ . fm .410' YI .1c). -..iN [ohlU N -, c
10 10, *P1 m C
m0'v- 6 - I'AN t60 %44 WmA.. m'0 - N
NPno 'J4f 0. PU-U IO -4 0%i 1- 00 F'1 ~ ' It. 41, .0.1
.. ".t..In f' i ' I -4w 1i. O46 , i. i n'A (c vC- N .0 N *, 44
0 0 f" .' tJ.o4 a . UW NýfI f"" I';L In I47 VI-r U- (P ASIIJ z ~ ao'0 m @ 1,14 -1 0.4
AJ ~ ~ ~ '' fn' .. "IM F r 0 - 4
)y C3 I'D InIC! 9
3 ~ 4 wN in N t0I' btll f~~m4P r~J iN ~LII, 0.1; r* . r4 * L. *7 ^1 6P* .J
%n In .k, in U. I i - , r- in t p Win -b in - L I V In~4I In Iý -1 9% 11 C n i p N nf t ,% C
C MO4 - -- i0na .4 fm III; P f 4'J fn 10 V4N -P "A M' Iv ^a -I
N .0 Nj -t In N6 '4Min t-
0.0 00 .ago
-. p-. r- p- t - 4.p -
tr0- wf@00 WO . oq. a 441 ab*a t, - 00 1
e0 r, ftN ow " f tv V4
.4.4 * s e C4 . . .. see .4 VIA -4 COB
a45.4~. aS uCI .4.4co 0IL
00 0 0 ~D ~c-, 4;riU %.LO40.a0 9 ;
IF .. J ~ U t0M ' w Ptd P wte 0 w fmd "I P4 Cr vi ~N40 ftr .- -g s u ~,14 0
-.. 0 .4P-u edWt 44 N in -aOrOOaa Li (0 oo u 0 zo C6 ~L
%p a u We 42 U.4 Cp a'*e..um a
"in 4-4 4J nVw 4.F. W NVEd
fl~) 4"Ur. *t.1~ "9 D~ cl oft cVS %AU
ala %DI w UCI'd 0W 1" 1% A'MP U
CU .9 4% 470
tC r.4 ., 0 -t -a4. i'd C24101.,9 3 '-. OF L a b c 00 CPtVc -'> vc: r. c:% IA .0 ** ; * . 550
kemu ~ONt o wa~ 0 .t0000' 0 ', a Co
U4 ft 94 - 0%.'1 n - - - L
'cc CP0U~ '4 -0rn 14-t CC f~ .N I', Zp.0;t. S fl* 2. 0 a,
-W 4- -04 'jý0. ~, -I %P- s h
3.P1' CCP CIA .74.i ': -
f.. 4Ow .4dtnm -4St. In" P- - ' .- r.0
41 %P P1~ .it I F- I coa-0L
vs..
4 - ~ c,,Ju-.~.r t~~t't..'.LU~U *.4uwK ; 0f * j nwwM p - I ~q t % -!l,- tCCC#
CA U
u~~~~~~~~a~~~ 4,- 1 U'or.C JM IC.1 r~r.Pm w .e.U 'C~~t k4Jf Jp 4YCA~tCI
m C-Ap Re It Nch 3691A 2 solo Fiso AJ26
-Mni I . Ill! 4A *0O '
:.n: .1 11 1*%Sa 3 1,19 0 0RI 0 0 , m 04 fIn a W%¶NI Il - aArS6 - I40 Lu 451 a a49~
(4a 0 e2fn0 001 O %a 80 m0 *6 L, 40* 00.4..
C P, IflO 144 1 00 .44 I40 WO, s A. P44 41-.4 "1US NIA Ný N.D4 a-, _04.~~NN NI
.0* 109.,.
1011 1 N~ 81: jic n .* 6
In,
.. 4 x .1 A 0t) i n
OIL.3 000 0"C;I C;, y *.; ¼ ''jj*!r'2
a .* . fo U A 4 m *4 .ir NC f ý4 1, * 43e *4 .N4" V% I*d0
.0- '.~
W Io104 014 ON I'M4 1" -4.0 MM4 404~ I
11 1 ~ . 10 n I * ~ .n c4of43 Cl e. r
-4 O 1 kP f. 4C .-I4 t- .% ou ca -0 .Y pm -4. Cý V. 10:wkL 1:0 0 1 I 1 4 11 ' iry 0. ag4 If" 1 i Q ` -0 f144.4 mO NM A 4f"
b. 01 , .4m IN "" -1
4' c: 4 4o0 N0
wo v-Ii Oý~ fns Ail. .471,10 f m en,~ nr'" t
or ix' m t ' Dc [.o-W 40 - 4 V I C 0!'40 ~ 4 .4 0* ** rn I O I ý rN -'d d f! I~ (I z
a 0 0 C3 .' C; 'al ~ '0 O N ~ 0 .
In P; 5-0 444SI. *N MN. *N I n 1 1ez In to M , In 1! .
Al at 4 .P-r T0- P- .-1 -0 -0 -4f " I 4
IFI
-j *. A
I C-Ap) Repprt NaL 3694sA-8020 I gs'.200000 ~ 0 O *
" ". a~ b% 0'n9 . 0 e 0 0 .ao LW Lgýoa 0 ln ra
,We, k 04 ' C;,r fw On .0.0-4 . 4m~ 01%0 *#W.. 04fN.. 0z0 *N. *No. !fN."
CO 0*, o A 0" **10o Mr .0 -f .01 o 0 0on a0 00t m 0.0 Mil .40 m f .0
111 W r0 mCcv ~op o cnj a e %1 nV-jabana V co 'A I- I C~o .,
10 ae 61 1 F- * 10 r C) r- in loo.d D Co F. .0 '09 .0 00 Da - 0A .- 4 mCjTP.4040r 014 .4% #- f"J~- in PN .oF- z * 1 F-w *'0O4l .Omi . M" 40 cm.v 'e rF- f o's f .0I~ A o fte cCW% O o "; " r aft f"I
In o"fl, 10 S ai , 0 in "a in wt ' 0I Oe% 0 W% 0 #ft V%0ift6 0 f"W 0'0mI rI.0m4
00 Cl 00 0ý 0 C; a 0 LJ ; c.
a!P, .0 'r I % p. 0. f' &. 0~. ' ti- ]4 4040 0. 'r D w%-I fA.n -m 16
1010 : P ; l.4 ft 4 4;1.# #04 o:1.4 ft: ONO NOý r 4 @ & -, nm
41~~~~*4 M MS."96 A n C MW,-A 00 , )0 1-2 f, r:o I~ 0) n
f5-3 ` Ca of3 ~.. *0 C'. r n c' 0.*0 00 10 *I 00 C: * 0 ; .
40 '0 C.- I
It .44-4 ~ *0'~ 1.* n 4in4 t .f fqn NON NI %l F1.. F-: 4 4,fm- F-# .0.*o l
0..' 1 CiC '.0 fme - m I NO. AA 303r .41v i .400 *.. e.. fen f -~.0 00 f .t
In t 0 3i f% C3100 Ni P4 0 1 *0.-. le 00 C ,0 0-0 I
* 0 C 0 # 0 . 0 tC . 0
a- . P a. in C3a ai
P- I 1;1. C, If. j 0 # r - ýC I..I 4;,Pr- A n .- A 4D a. 10 a ' #g4~ w% w%"-j - f t"n rP .44 0;7. 00 dl- O o. . 01.10-
d ul 4- ýth f " % Aa4% M W~l : N # " * n 1% a fa 0 C, o%.O Infm0! e 01%C% ft a. 4 1M.e #4; o n fl' l 4.j4 b eflo i d 1- N t F4 - F f*.0 -..
.0 No 408 il a0 Na0 0 N 1 0 .. ~. l -. ,.
oý w 8 0 0 0
mj. F' Idl 101 .411 *l. f,% .4t In 4 F- *-. .:% -=- ? *.-- . 0'. ' .0 wfme4 *l 4 m4p #Ae~e mo Ino fm e dCI N0 N-o N' N. 10
ON~~~~~~~~~~~~~~3 "f34 lfl4b1. k 1.O - ~1C .4.0'CONI
el C, elv ' '3
414 -r #ft 04" fn Inom .e zjI ..-So t-- f"?P 040 F'(4 OF
c c ft a 1- l c * ~ 0 . Ioo e), ~-oo4 -oo Q
L4 00 -r A 0 01l -0 I er)I 3 .33333
on (7 ft 'I
Fa N 4: Jt- Eld.%4 04.0.40 1 0 ' 0 i.N0D' cl.O NONf oN? ('Jf,90 C'., 4.? iNO 1.43 400 W%- F4 .0 1 In- m4~ Nft dI ? on*' -1" j%
NO IW.0 .4 O- NC -f P. a t.4 M% NI' N 0. f40 N ý 0 .40 F" onl 4L 0x r I
es m- Nm :,o"~ 40 I .40- #m 74.. o."40 % ý W% Fý N4 f.4 C00 i 0 t) n' 0 ol;0 0
01 ",- **."1 '; "~ 0 0 0
0'0 0l co 4 N v *F- 0y ao') co V.F 4 4cri m F-. 0 " () " ' I-- C t N m% f .4111s. c0 0r C,- I.4r
43. a 0' % 04 P.0 0 f 0It1l -r 00 01o GY a.0 0,NIt 4 0 -C I I
w% m4~ v...Ow'mc
(o0 r r 0'ON 0 .#4 3 fn ?? 0 f'C r4I mO0 -C4 '041 m CO f0011 .fqII
10 N 0-4. W IG I* *ýo : O ý il 10 !iI 0 V"% fm
ln n Ic f4 4" f4 hn"yo nfqr l % fI Im .I R
f~ a-. -m -1a !- mD -jeqco V nl F-6 n W4 l CO;NN r 4 e 1 4 C>'~ " 01 62fýU I " 1401
A4 A4 -4 . .0 . 4 . . . 4 .4 .: . , .0'^1F N ý 0 n .61 .0: F-% In 0 1:f0 0D 11 . 0.:ZI, . 0
-4' 't
EC-AD Rep-.t No 3694(A-8020 "Ps A-2
ftIP QWI a,& t t6E. f"I nap WIP- Le .0,P -0 a 4.
OV0 00 05 .0 0 a ao.0004 1iN ., 96
I*a ft a1 .01 @ ' W~ .0 " 'O 'D 10W . .eP a -4.ait3 *PW4 0 - 14 I.- .4~
NWp 44 on* a*P a4 -* P-in fn.0&wIV- W4 .0 1 :4 -T4 -
NW d .409 3 NW4 e .. 4 PM'o0 inP -* -- O I.n 4 -: 0 -. O-'InO. 5. .0 An *1# 0 k " !a W% I0.a "I ~ -o, .' ý
.M: 99 '9* 0-9. fta 9 9.F-sm . a em I&~ e. vi P. pt *.4 cc M1~ OIt
0 ~ ~ ~ ~ j~ ov *)o"".4 .-0 0 a"t " 2
0,146 CI In C
~19 35 loo W%49 NO P.4. r-) It 0 O 4 ~ 0 Nlj 0 3'7 Z N rol v P'J,.% 0 wtC ~ ~ 4
0~ Ub0 , 0 0. l#;ý.10 f" on 9% V 4 :4) fQN P4-o 4 W V% .. 4 NP *Ga o-4 m "i--4 ID co.
a3 .10 69 Nv "t om 4" 49 em' k" -.' 91 -f ft f" 0, 1^,z 1 1:1 48 -f old .4-9CA I ( ~ 0 * ', ; r4 - C.,*9 3"I 00 Zk .. '. ft .50 'bl0 c 3.'
: ani .*a " ! ,. a " pý I
em af 43- 0aW In a.W%
969 *9- *WI9 .4m 9C *(p9 r0- N0 *w% ftt na %r4 P 0 o-vr . :- 4.P4 k"NW Wl .0- 10 4~44 W% . % I49 WI0" r 4 9- 9... 4D %MNo ' . #).OP9
.406~~~oo -41 .-.4 ,'9 N4. W'01- ca- '4 '0 '~t- j C ~ 4 .44 .14 400 -4M 0i 00 't, le), WI n..0 .~ ~ 4OI
0 A 4
m 4% V- C3P ~41") r J I P410 NUD r, o n nr !0%- 44m9 . 4 W O J14 t -v co oc
EN en3 f"I 6p P4 I. - p- N o U% r4 0% a co .4 fI en .0 NO % NaN -" -
.a~1- 9N *0'# i9-' .Cr. 41 Y. 0- f* 4 ) .60 .-0,0 444WIt ,.
rI- cc,. -t 5 - 1 N4 .40( 01-- co AF WI.- 4) & 4 .0UN so400 WIf'G r441 .'30 do -Nwa AP.430 (F Nc .0- m P. .- I w -- P-.P- i- r
Nm .en %A. .i N 1,: ^19 P- 4.4 1, 40 Z'rqon i- r94 r
(3 le kq. IN .. Ili C' J% I 'a , 0b0 nG
~~b041 fm4 M34 *.t- ccOO M.- It. P-014 40 * r- 4110,0-0. *3( ~ J>44- No Ga.~ vo 04~3' N0- GaND P-P*.. t.r4- I* I *-- 9 C
*W C% 9. a * a **d 4 . 9 4 - 9 4 * *
WI' 4 ~ 0.4 41441 rC'I O0.t *4 f"*a4W, W 44 N '0 0 W0
IITC- D epawt k. 369'A-80oO P~ga A-29
ON& a f !M i*g 0 V *4" ..0 '' ft.
0. fmC
* p 4pN.4 4p~ 't %,
~~4MIM I' ,%: t-P a~. inj.. Ila?4 4 m P.4 *
4PU 440 t- PN14,N 0..44 i~hn 40 * .a10 .in
r.114 go 0 r Wb 0 .
t % I n 1 . It 4 QI0. b f4 4 - 1 f02M. . 9.4 ss8 '4 P.%r.CP 4 4 .s04.4
N Q . 40 A 2 r 0 3~ 04~ N*-4 4 1in UN., ft 1 N 60 1.O N l ( .1b C I yS d* 6
*~f 6p U. 4
14" g4s f% -. 41 N .s NwQbI4 C% NC 'a '(%f)4h .. C -f- A 4 fp
C4S ON4 .. 5IN ro pi ws Sz N-Wi SAN -n1. 1%-t#
AA #C N a IN 1 a -6,; .CN II j .4*,M .4N ' n W 4 rS C.4dP
4; C! a 1ea0
el. 0;f9W% W% f' f" W~ I
'r 1- -0 . * 1A
1-% . 4 Nlift N O@N M IO a S. (f !4C f9-C %n- "N ' 04 6iiONe N 4l OC. 6 4 Njs ýO Ostil E9st 14 L1w4.6 `.t4P 0 r5 .i 4 sfl.f406 s-4 0 NI -54 -jf -0 II4O N-4.4 W
*, 0. 4% r41 * .
f"~ 0 !.N r4 *..'s *Irv 5 7 . C W%35 N 55' *CcN0.6on P. FM 403 P.14
N4Ua P .IN Nn r- N0 M N 40 N 'P aN 't~ N4 W% P.-do. NN WP.
P.4 N o ýA 1 AI NC.E 4 N M q-N I sO P44 m'9 C4a ly.
f)C 0 N4 vIN St
.tspC% *N Cs~ C.. I*~ N% * in N~*
rý Cc M. 4 . 5 CI 4C 71Os f 4 a ONs ;1A m% .4I~ :1~f (4 '9 ' C 0 inI # . ' W% ~ r4
No O r A4 A "I ##e *.* 1^ 4 5*`I -t *u00t r 4 *W
4 4 l.' N N l 4 C'4 Ca y NiP 4 C4 - 4 .
m m ~ 4 04 4 a *d 4 .4 r. Ol d"
'5 .. 0 no W% f Ia-i -
AI...s ~ .......... .'A.p''A,;,q'.uu'.A.6 4;4;
IH C-AD Re Ort Nl 369_'A-8020 Pagedc~ .3Reprouc~dfrom
fi l I I
F. F- . % .T. E-.ShM
0.Oea.4.0.e 4O41 0 s CO&~ 41 M I, a.15 . IW 0l .c p
0. ~ ~ '1 oo ook. 0.Is ** 444D W% Ah
.. !t- .~
*.Snd "c #O.w4 * C_ # ,
#Ml .. [email protected]%-4p.VI *S ' @4%qn 0 MineaU VNF. .00 C" '0%0 -de MS-j.- MoZ ddr Inc... 0110 4c Mo "N l oA
09J 4 s A ~S0 9I 4 f" Co to 1% a *nw d4~to pW
0 0-1 Ce.s f'1*S -t C. -. ng.
I.O o I Ig,:~~or " I.ero~ o'eee .'S Mp Mo coo-. -~. ' o WII" 0%q I .'w 111' - 1-
U 0 .. '" 4 0 '1 0. "C 0 tcM '% 40 ap-o ý Ir c.oI0%00 BI 113W
w U. .00 Offew0I4,.MAD00j 0% e a.W4N..t . d% Pf G..0 ft i0 IIKW6 N ff 4 I b % n o _ i M.. I*If4 N0 O C-4OeOmwt 00 0 4: -ewA ,0N.I~ 111% a % n w4 %.-"4..
'.3 .8 ~ ( 00 0.:e.c a~ OC C :g. ' ': 9;l -4; C;EJ 4- - .4 ,; .4.~ -13 Ir" 9 - 4Q. -i a
cc ec Pc aoo c e "o-t. 'a, .11.~0f-E4-S s-I C"S SS.11,. 1 7 5 105 0 i Ii fgt,
O-Ii0 .4O~f0oeft40. 2m.!p 0% f4 13O
r% 1 710 0 aA. 1*4I %
on U. 0- 0..0..S1' 01" %."J o- C.ooC 0~~c cl- ~ ~ io ~ -i..
4~I :0. O 00 5 4, C 0
s Ior , s% a #f 1- 0 'o .0 p- P.
'5 P OR C.~5 Zdjftft3A ~ q
AS C5- ftPl r- 'P3 tl.~ C-n ; 4;CZSIL~~I' I 114 . 1. 1 1 1 * *
O'sV~5E CF.V a- 9 00~P_ -o I0 % "u 40f n 40N..& a. ý P% O.C 0-.0P-~ Oni 'D nNi . -0 . f -SfiSSSSSSIrIfmSSSISIftAS>7CPo-SWIS
0 40 '4 0- 0 *S................ '.. . a. ...... :s. . . .5...... ......................tS !G 000 ItA ~. . .. - ! III4 . 0 il C! 0z % .. .-~.4. .~ *.:'
9; e; co 4Se * 3 AC.. C% -D k% 4 .4 14.! -4 -4449
ft VA- .4-
C~i C, eId4 %tl 215 LOl C- C .SV C a 0 IA
AR C-AD .Rpi No. 3694A-80OO go pgA;31
to a 1u ..
wi P-win, ~ tU P- wU .
UA 00 A0 ~K 0.4 0 4O~40,0N0.
Q ' ' IC
ov 0 1 ft i o *0.0 fy C ,
.00 v-IE Qbw p49 "" t 'r VI 0,a InI
us c C 00 ~ i*t
*o~ ~It .O~*-~0* ~ r~d*' .U' ~ i >1L.. -. ~ -wir 0 ' Qu~. Vt0 Q.
int aS : " 4) 1 '7
" on '0 N "M
04 W GO cu~
10 0 'O --b*: F
I.l
P- A4 co44
.JýKK 00. M4.# *0 41 )31~~ non -t .0 1M w 0 on , I V-6
* w i o -6 , * a -a .' %J .2 , -1 C1 ff10
s 'I elV. ft ' a IM '" f"0
w~~~u~~~J ' 'E ; t ' I~0
nM ip 0' '.f 01 .0 r N
3w (L. 7 It P% "!:U i~
AVEP r-4 In~i .- C.t * .4 141 ENA 0 W
~ ~ I t~ .4110 ~ P.4 0 0 .U'N ,WI A;
QI c *
4 0' C4 I*7 ftOP Cn@ e~rj N14 .
EJ U f, * ' * 14 %A N7b -t ".." ; A' IJ
4*P C2 C.~ F- r .t !Z -
4.' 4P' 3
-~ ~ ~~~' dl 0 0.** W% al1 %Cd M ~~IIo.- i 0
- .- 0 ~ ,1p -V %n C; c4@; .,1 V .
%n P. f4'* * 0 . . * * * * . 0 [ 0 .
0010 0-0 N n,*r PI
!f *% r* e, est .1 eN *9 QI%
0L t.4 1U.. . . . .
.t 'o 3 'A
q'
VC-A Is tcL 369.*A-.I020 Page A-3Z
Cr a *I
af IP 0- a-0`
* ~ ~ ~ f *p - *..*r
.4 , 4
-- u I
CL n
ZI - -1 C. Z C1 4
0-
U. 1s0 -4 f e
dc , %i 0 f :c
Ic c
It ~~~ nO j 4,', t
4e wa.44
04
-0 -o % .0 CI I.I 1 i o *0 ** n 01c I- -
cc 47 IT
1< in f, 4A-r p 10 a),
40 -I4
S'a. 0 Z* W 0
LLSi
NC-Alb Re it Maq 369+.A802iD
A* #
at. 0 6111 poll0 c . *t * 4D
on no E4 .. o;C.P.0i~
Il 4D~a (I.7 *t1 f
~ ' W' PN4 O w *t *' Z4VOjO ~ 1* *9* E.0, Of't' ill0 M%~~t.4 AI
w SI o 1 0 .0P, . 0 "0., .0 CO ý -1 0.4 "~I 4o~ ~ Old2 I~
C6~10 0%* 00 4pp CO.#nof -F r i r
.000 ;
CI~ r* *e *v* .v: r~ ~- ~ o
~~*o 04 fl- 01 Aft 0 . 0.i 0
4011V n ' -40 di 4%i -00 0.; 61#do F.en r O
I .1 c- . ..40 C. :0 0
a~
In of eI..I9% P o 1 0 _ f d
aP 4f.' 4 I'* " , - 41; 4i%4 4) a 4 O - F- l10 0 A % ,1 000 d l.%
40 P)
-M ~ *m 0- V41l" *00 -W .C% I ll %0NIý"
I . 0, 40 ; cp 00 1' 0". 14'N r
0 All a 0 .
.0 .0 C-4t."ý ,
.1 1I - f %I )pl ey * ýA 1f 4 P- w -0 API. 4 C' C M
I I aa
,L..Jt U14 1.'C -10 ;.P
.~C NOI 0. P4 0 0 a
.4;d V% -) (0' -" &0~ 00 us -r4 0 I
1 .0 P_ 0 V- 40 -% ) 1--: _-Ia P 3 C. m F-- c--
A I
4-4i
ft OIC 0 W.2 0&( lIr . , 0 M ,
1-40 --
41 4
F- in .@4P0%z ,4
at NV14 orfl a.C O N
f% 'A
UA. 0.0ac
Li ~ W n- 6~&l 0r~% cNf 441 -2n .cC. C t 0-4 C4' C , ~C46 0 W4P- %J
a ae L U. .
:. CD -C
-*. Nl -4 -l
Ulf -4 .4-
4 4 .
I ic* I l t.N.- 369 F.I A 34
IS CIO .10%'e
,l 11c, &
*VIP; C0 .t
a l;o ý si 0'' ,t • .,el F, ae
S., , , ', .1 o e *... .. .l 0
^ 0 *~~)~ #,o IN on
r . OPP~ NoE P4
4i3 .%WM , ''.o
OR dew% 000 or-IAL 00 9%l • iIt 04Pl 4 -%W1
4e0. ea l , .0.,•, -
w V100
m a 0 ! 1 2lo F- -'
41 C. 0 Ol• 'l ,P' ,,l" 0. m
W, , n• '#
114 W UoOI
C C * * I (1
14. W"0 4D~ Q-ft. C.Q l. .0 in4 6 - r
'0 ~ CAC
,oC'. o<>o,PJ- = ,
I•" I I Q2
a'0Ff0C 0 C'l f
-. A. 4!k<--
.- , ,l
S.-
VICC C+ ++f +- III *..
II~~~~I n w' -t ,., ".t: o:
S3, * 1 .* 11
IIII,.
Ul ,
-" i I = •. - o.'>+<.o<,,,o, -<
I •" *I.•!• 4 C•••)" "
I' 5 ," 0"~+• lz 1
0.
IN AO~ IL*"" Noý 3694A-8020 Si AI
.1 lln 3"i t
.;U : a ~ oft * '~ 0' 9*v1I.@ .@ 4 00 0& rD pba L C.
0 V of4:4%tN .e0 p- f 44 c.j9 p- 4-
r0 C0 a .. W 100 Oi,V 0 10
-4 -3~ so P4 W% 0ýca4 .401 Pý "C 'D onr- .0 -0 r~ ~ ~ on. 4 *sAN f-
Pit ..4sN2 1 1 t' s A't- 3- U0 s1.4 -Wi isA0
0-4 ~ ~ ~ ~ f In. W%.- , ~ i0 . .I-
9,9 *: fft 99 40 9 en '.I.
4A U 4 54 A* 54 0 39
't -m. r " et nM
a* .0.30 N s.4a, o -M 954 4 n 0 O nft9
esAlOa 440, C% * a '0 f^ sna-0 Mon t- 0 0 go 0'o-
I4 I I
1 ',f0
1"4 .04- ' .6 -
AA'. yo5 1 o
W% 4p. -01 0 0C
w 0ON 0 ~ 1*- 1-0 W% -f v &.4 W w E5nOt ot r- I-954 -4 -- m .0N e 0 m n^v0. 0' 0 r" C.
L4 to:* '~e 4N4 N Ne'IJ 02 440 A00 luS N'
w *'0 .4 10I..' .. O ~ i '
400 N 0 W' np
V C U .W 6 U . 1rN1 %
u 99 fmI 1 i 44 1 r4 I I 1 -4
~~~~~~u -- - . 9- .
I4. P; 1: "1
I LU
P- do to
~.0~ 0 05 & a
4 NO-M**0
Wý 00cy
U.1 0 *
it I
N r4b
-4 W% fn et .I 4
4- U -.w0 co f-W% F- .
t:*u*~*'h i ~~- L) ~ r~~ . C e
C) e%- .
1. CI 4 W% 4 m. P
IItI i Iý U r I ~ .,l
LU ml ON '0 P- cCL 4 *.
TV
C-AD Repat o 3694A-8020
ý4 f. *f' * P- *P.
om P- 1-.. f.P -- 0 a- 4
fmI e. N- Nf" N P. t
f- f4 a,0 *I- W: 0 %
.. as1 4N 11 0- .A4 m .P-920J l* 4 fA o UN .ON D .0 on .~
fK t -. to a In N .4%^j .4 % N4a
-0 e- C,
30 ONO. j- 0',
P~'J NP 4O4 A #
* ~f a~- '*10 WS- W '
1- . %5 U% P.f%
CP * n .. F4 F.4y f N a Wo
*~e bcM !a. , P4 L 4 OI 4
0l 42 'Ci *4 C.N *P-.P- t"4 .a-of* 0-QP % n" -
n. ý m~ N 'C ..- i4 flOc 4 041 .4,u
.J - I-~ N 7 0
O*d doP fo, ý1ý )f .r- ,..1~ ..*;)g r4~U g .44 N *0 N NO 4 W 0 rp- .o
f~0 0. 0 -: 0 j 1
* 9I W.
CI OO * a a
el *0 o a : v a, N ~ "o C4 43I ~I 6 -tIt . 417 . P. a. I
I: -q. a-~ M.4i~ ON? UNI-
o V 3 C; 0 4; F".. 4iM M~u~ r NaN ~ ~~~~ CA aj. Pl - -
IA 0 N.4 If a . AN N4 iN
~ U) ~ J .1 * *
0. el F" **W44 31 I
=2 -* no .1 0 .- C W% 4 m WE i6' P m 01 nf. ý I.- =
aU M 4a a, 6-a
j oI'~~j369 * 8020di
369A-02 j38.. 4hS
A.
*40 I C k- c1U 1.
i n n j. n i , L
uj &: .
IL 0.
40 N -,f- ilit%j 4 5
U.I. io iU. e '--ý -cI"' X: C4
C; ";z
C. Iwo ,
'4-j
*u P- P- 8.
%W. too4 w~@ %W %0 f-loa~w%,
of- 0 1" r.I . C ef
Wl 'We- IV"
as CE m Cl 0 IC.C -of tv e- .4r NtC
.6 C f, .1 C -0 f r 4 0. ' 0 r
cc Ir .E: f-0~ ~ ~ Cq%~ % . S.G crc
OC r.'~ I-( c C-c
%a~~ I. 4 -4 4 0 Mcc
si %.j *P4 Ofte 0 -. W V
*r" F_ 0 f" *N P~
to '4 L4. G..o to r. Vo.l r- N
C. ).
r* Cc 46C cc
rN. CNQ Cr.* 4M. 4-% 4c' E¶ c u
4S IN,0 N c* NO. . 0 o 9O~~nN4 W4N 4r I.N G~i
0l c 0 cc
r4I ' of a, 1- .0 o-r 4% ' N 4.1 v ?w 0.0
I. to a, f% P. 0 wf~ * N I f- m 01 =MfyI-t f_ C 'N in Nc CN .L O V V
B.C I )
*i I I S S 5 1 * -
0' -_ _ f "MP - % cI.. .J: C. 0 '
1- * HpC-~ Re;)r No.69, A-8020 -pig A.. -.. 40 U~si
*k 1 .14, ~
leo a4P C.
*'*@ ~~~ ~ 1 r wU.~f~ A c - c .0..- .c.c or..tr It- C -r *etC I I .I
Ca C c CfC ~%d %n I %- -. C Ire C. Cce c C. c C. . 4 c..Z
I m-F .9- c 0f nI
.2j C IL rr -W 6 f. cfLI .. 0
c I l It c * c rc C.,* .c c ... o
P 4C. P- * '-L U'.. *i L C t%
It0 PC 7 ~ Pt r for,
*, ,, ..U; I.JUc
w~~ at In. c
* ~ ~ ~ 1 on4 .. 6~O~4
CW c II qu .: C* *. I tr * -
L C, c C
*~~~~~~~~c U -5 J4~ 441, or tý or ;41L.C. . 1 . C3 1 C: C
W, Wk 424 r-I**'-q C4*I c N' Ný r, r, A i 3C 4 M V.- ft L r-.a 4 . Nc I. . -W %c
a P-
CIIC O EC PC, V .rq . O Nd V~ O ~L. CN C., cP. COPC c- 'C. j~
w, 0A fm L ' C ' w
so c-~ .'~ 0PI. .)~ C)P CI ClcC, IC - 4
V4* tC v v C. a w u. j f- 44- P- w *1 %C C.C44 's~~a cr LJ. Il. C. ft r .. %fC. f.".ý lr.)~f fý? he,-4a 2 I;
I e i r% v U- Uf W% fn P UN U PU I Id% .8U
-4 - - -. 4c 4 -4 -4 -. -C - LA 0. 1
'2 0 IP- r It A 0
HTC-AD Report No. 369-.A-8020 Page A -41Y ~ ' 0 'a 0 to#~* .0 00 0Wit 0 C; 0 C% 10 a
* b00 00 claw00 010 00o 000 coo00~4 .0 *00 *0 *00 *00 4 #01 4@01 0 V
'Woo 00 m IAI4 wo 0, 00 000 1~- 0 v --a Ala @ -10-~00 0 V0_ w0 -00 1,-
v m C300 00 as0 Wo ca 00 00 00 0-0
.0 000 @@00 c; 00 Q -o 9co Vý 00 0 a0 aY 000 0 0 O
N 00080 ll 130 3000. 700 00 00 0
!3 so o"S coo 000 008 000 000 000 0.
&a.000 0010 0000 0 0 0
0 a o: 0. 00 00 a
00 -ad NO00*p0m O I 4 o * WW 453 31 3. 90 .p00 007 ,IIP04: Z 40 0 0 O 1; ~0~
cc a0 0 Dowa @0 wo r4
IL ~ ~ ~ ~ ~ @ 400W s ; -0 @qwg' 0 v00
0 40 a
N 03e 0 P, c 400 Nlow I rqr IC4 flo~~ 0 0 0C ý 0 4 b Z00
LL 0 'f0 *0 qO T 0 i0 WTnu t-.ow 410 *~ -0
00 D 0 00 0O0 0
.~ LL. ~ *p- ID*0 * Co 0e .0.40 *Po '.0 *
.4444W 9 pqL 'a~ WD 4 8:, N14 m4. Imc 004 W
4Z 'cU4 aa too . 0 140 a0 to 0 042 #mU u 4 0 a0 00 000 0 Q0 00
* aa010
-Dg 0 4- *'w a 4 .03 *4 .c*0Q
400 NO -''8 N4 0" 11%' a~ an P_* -40 -eoSoQ K n 0 P4- 4WQ 4p 0 r- ~0 o ar0 r-1 0V WF4 W V
-; 0 00 @0
. 0o P 0 -40 0 0 0R o 0 0
f" 'NO '0 cc 0 ' 0 **@0 '00a cy *420-"-a %Po-00 CC ~ 0Q Q~0 CIOo oo C C
00~~~C 00a 0 0 0 0 00*~t a 4 a.S
K0 a C Im 0do0 0
- 4 3..ao 'a-a V V, -o -o m' -a r-aP g 0 40
C40 i Wou. M -W% sQV .V~ 94l' .~i a ~W N WN- a.1 04-"44' ý~ -* 44'4N -. 0 -440 .40 -"40 ý4 0 4 -4-N .. 44W
r.0Vj W 0 0 r4a Q a C 0 0y e44 r 0;4 0I 0 0 ,
ID.x 0 .- ) 4 -
4 0~ 4 Q0 L^ a I 04- () 0 10 v4- 0W0 040 0x- - 0D -4 CaW z V.-' u0 04 0, V 4:;p M-4 Q -0 a 0
EBest Avc~iabeCp
H-TC-AD Report No. 369-A-8020 Page A-42.0 *O 0 *0 * 0 500
a'05 * 0. 0. 0. 0.
4 0 a0 0 0 00 0 0
S* @0 0 SO00 **a 00
O0 0a we 0 00 .00 00
@0 10 z@ @@ a 00- Do a0000 0@0 000 @00 0990 0
0 00 * 0 000 000 @0 1
00 Im 0 a 6
00 w 0- 0 c.
000
100 0 we 000
04 0 00 0 we4
0o 01 '4 U 00 zI'00
0":~ :- O 0N.
si t q a o0 0 0, M u eno
-. o go Mm g" -0 o -
00 RO
o 0 0 M 0 0 40 00
0 *P *0 9-d0 440 0:00 00 *
Z41 *0 so
0 0 wou SO :0
ko~~?1 so s- a *-9's
#4 . N4 fm t";~R.
* II I I S on
149 10 0 f 0 ' *00;0 00 0 *
0 0 0 0 0 0 .Qf
1 -4
.00 .00 CM4 1P00 sinO .0 00
9 00 % b1%. -dOo i ~ o . 0f"4 -W "i*Q 4-1 -00
.9 .0 O 50 0 *0 4 5
0 a 0. 0
*0 .'50 *0 50 G.0 50 4s :0~40~00 0-' 0 0 04 0 P-40
0 0 140 19 4 0 04 00 0
5*
w go42 v . 09- t4I'-0 LI "F'-o Ug~ aNC7 0 *
6jrQ 40N f 0~ OND ONe ON ON W%P3 .. 3'Q v -4
V ft U 9 0 0 0% 0 0, 0
Bes Aailable Copy-D m 3o a 3 C3 C D^9 > w- 3- L.) e t
11,& C) fn f" K e
- 4 -~ ~ .4cc
HTC-AD Repo~rt No. 360-A-8020 Page A-43
Al -0 0' 0 0. 09 sa 0. 900 us 0 0 a a~ I a
A cc I- 000 000 o00 0~00000 000 0-00 000c 000faP.x a o ('cc 0 .@ 90 v0 '00 0
fZO. r. 00 00 00 ft O 0~ 00 000p "Ia0 W ~00 aQ 0Go 4;;. o ) C11 w 0' 00 0a
a 000 030 O00 000 000 0 Q0100 @00 000) 0
Wa 000 00oo j 000a.0a 000 00CP0 1 0 ~ 00 0,0
1UJ 0 0 ja ao o CA
* 0 0PO 0' ow 00 00 up Dla
0 s*09 el:0 o'.o CVIO coo 0 cooQt.0 aOl 0 0 0 C,* .m *0-0 *C3 C, s 000 ect . 0
N.- 4 Si.4 0 0 one P-N 0 #0 '0 CI 00 ~~000 m -0xu -JE -00 -'@ a0 ~00 GI50 41 @ 1 oo ec U v 0
Alt. 90 U0 40 %a .0 08fW 00 o 00 00v 00 00 00W t 0 V -0
In0 mQ 0 -0% 0 0 0 40 0 0
"a ;t- 1."a 440 040 M4 100 1"0 40 "W0J A x min . N4 f-tO 0ft 0-* 04ot08 1 In 4-0 0'0 % 4W% oo '0
V8 -i C32 X480 "00 MOO0 Ran0 Mao "of #4013 .es 400 NQt)% a0 . $0 *0
@Q *~ 00 **42 . ¶~-9zo I' ¶
0 0 0 0 0 a
0 it 1p *0 W940 -0 Mo P0 M 0 m
n "i 4! nVW W0
00 0 0
Z) sm0 600 O *0r CV. 0 . 0 't^0 .- Cl990 . 0 NgoWa 'a. W94l #40 'Q-O Woo Pmo 4 Wf4 V .-
cc t. -0 9 0 9 0 00 9:'0 *on la 0; L'00 M' 00 '003 AV 00 00 00
ýU0 0 00 1 Co I P p V40 a 0r 0 0c'I I; U j "I j D
*~ ~~~~~~~~w ofo o il 00-00i r Ei'0540S
0 0 0 000 0 0 0
.-. 3 g Di '000 .4.n I1 -0`0 r"0 'a0 'Do PCO ~40- -4 X* 10. 1 CP-t IOU' 600 f49 000 0.0 W O Pa0 Ot010 0.94 0 J Q*' W .0 9 0 to .4.1 . 0 . 0 *94;1'd *~ U4". 400 U0 %30 ~ .- 0 00 0* -0 00
vie in 6 0 0i 0 N 140 0 N ('0 0 a4 4
S 4-Cl a 0 "n 4n . 0 0 0Mo
cc- 2U 0-ns lw =' -91 0 0%O'. W% 00 000 r, 9 a NII 0 P- 14' 4'W --40 mt A "4 4ýMUMOMOe 4 0r For
a %. . 0 CD 0 W 0 0 0 .0 01 0430j o. a 0 0 0 0 o 0
a. 0 C.
a v. C-3 0W`Q 0'V M1.o0 0-0 0 -qtp % 000 - In0 ooo Im %-C = 0kcc -- y0-iC ý4 oou oIp I-o to 000 z O('40 000 40Q 1 -0 C.r00 0m
Q ..)v.J.J 14.4 431 1 C3 O~ 0 0.I40 P-41* 0.00 r.I'W fm U a
4V1 I0 I. I cotI 0 t t 0 4
40 9t alrC .6C WI 40 -C UP 49.0 t C7 t
r40. e a- - 9-J CM V.4 - -W%
HTC-AD Report No. 369-A-8020 1ýage Aý-44
0 40 0' g
* aa
000 @00 0V
00 00 00 10
lo 0a *a a9o0 og0
1 0
@0 Won-0
00 00 00 1,0 0M
. 0 pal Ow W0 OP-
-* .. . * 6~@ 0 0 0 '0000i
CIO A 4-w-a ra... 419-00 i r- 4r W%0 o0
~a a 04 W% 00
M 0 #4fn0 Wi
4P Mi 00 Q0~' 1; *0 .j t
AM 0 Ao P
10 . isis CO PM0%
00 ~ ~ ~ 0 IW P 10InsQ
.~In14
C9~~ ~ ~ ~ isF " P - P..
HTC-AD Report No. 369-A-8020 Page A-L55
4 .0 .4.2* .0 0 4 0 Soz. 0,; 0- CZ 0. a.; oz V .; Qj
0'0
loo00 NO ', 04 0 00 caIS 0 a ' 40 0 -00
I'. gi *@Q 4.806 0 O0 .0 11a- 0~ mc aC a0 woo a q to a 0 0 IQ0 50
*4Z 0C C *
00 a a0 J00 Cos Oso@o 0 00tto ~0,f 00 00 0 80 w5 0 .4, 10: V ,- o 4
:30 00 00 00 u 0aua0s 0: 09Is0 S@0. @0 4.0 0.0 00 000 1
* a *do 0 Z6. #;4 4 * 4
N0 00& 400 00 Q;ao a
zw~0 0 0 118 0
:: 30 o
4* in 4 Z44
49- la X .0 O 40 "0l .40 "'@ ' 0 au903 0
0.0 OO 4 40 * 0 4.0 @00 . .
CD "P*o two0 ff94 4100 Of40 40 on 'a 0 IP 14 V%.4ww34 .490 m4 w'4 vu 4 low: :ft re0 6.0 49 ~
*~v an -V. oo 03 ~ *
O0 0 0 0 0
LL 0 040D 0.1111% v f0 1 0ý 01-O 4@0 0 .4 9 9
~~Dow .4-4 z90 CIE 0 0 -~ 14.49 10 a 4r~
jz ;: 99 .o
4D 0 0 0 on 4D9
Cob 00 O @C
WI in0 0 0 0 0 0
:0-
on *fO 40 *on 0 N 4.0 on- O.O 0 f"40 ME
068 '0
jP 0~ -40 '4'0 in0 4 0 -40 on00 Z-9 ; r9- 0 4NW ~ oc m a 1-' -0~ mm" r o In z o mm Po 01.0 o
P0 OD C C40f 0 0 P40 w*0 P'0 Pin~ 00 Co 1 C 00 00P C, 0v 00
SY o- C3 .0 40 o 4 4 40
4 0 0 0 C 00 a
0 : -L ýa C.10 a~ *-0 W a Co0 "% 0 C. m430 .04 P4-40 410 4(,11 v .P- .9.0 490 0. .la . l .11 00 0) 0 a 9- 0.4 0ý .
; C t 4.v CD4, V0 00 V% 0. W% w 0%C 4D -. 0 wwo F O le w(a)
1. 0 6"t *O C3, on %n -4 W07 o1: .0 0 400n ,
-J 00 00 r4C; C0 00 f0 00 r0 0* . . . 1 .01 o,
a 4l . . n 0 ý 0- a 0 C3 am 0 0-C bV ý C 0 0 o 0 0- W
44 C' C3s 4 0 "I0 C W 0 Q .0 440 440 a 4na C a0 41, do 410 43-Z 4 X 4 I %A.) ý41Q-* 4 110 0.0 0.0 9 '~
I. ~ n 0 m 0 4 '400J j.4 4,4 c;4 9.940~~~~~~c t I~ *r N@ 12 1* * I'0 * f @ 4 .9 *
0 . ) 4NP
4-"
IfTC-AD Report No. 369..A..BZO -page A,46
-t
go'!
24,3PUWW00 0 0
*41 *0 .me -C.
1..0 4w CIS
4~~4 4 a a Pm
OP4 Ql f 40 ~O0 1-d 0 *n p* P.* V me moo 0
W.4 4"c :c R o oin 0 Q *a *19
Obb
lm -o in -0
A *l too .4c lot0 C44 I0 0 0 03 0 .0
~c ~wc~.a -'-a i-o m~ z
in ~ ~ ~ ..0 .4 .1 ~ * wi,* ''
a.a -a a - -t
C, 9in 00 t0 W1 0 OP'-d0 W . 1- )
-ýTC-AD Report No. 369-A-8026 ;4
14 *0 00 40 ~ 9 ~ p~NO 0
10 880 '0 030 900 WoO
00 00 40 a A; Oa ~ 0 ~ 4
n 009 :101. 0100 *000 00s 42 Qa fi 3 000
003 0 q
0? 00 00 :0 0y 0 0 OT 'I
0 00 0 00 0o 33
a. 3 933 00 04010 000 0@ ý ;00 ¶3 av o ;oco 0o ~ a 3 a* lo 402 :o 3o 2 I
loop @0 00P 0: 00 UP00 008 0 040 SP 00 %a0 iO
100 nn0 0 000 o 0430 09 00I a* 0 0a 00 * 0 010 00
wk @ NO0 P.0 00 f- 00 @0
w, in a ~ a U in a o aI 0t
Z.0 9 al 4;0 w.0 4004 00 W0AL 04 ff4 ~N 0 0N 04 4I 4 10U
$.0 0 0#ý F- 0 0 00 0 0 0 ;0 ;g a a
L&. "ft O o 000 00 Of4 *CO 4
Q 0
x~: ;23 WO o o306 U to .4 00 100 0000 0
C*1 * .ID @0, 00 -0- a 0
* 08* 0 0 @0 *Q a #
w mo a a a a 00 0 q
qQ -,c 0 0ca 13 !
I- 00 43 -10v-aaiJ 'a 00 .0 0 .0 T .00 I 0 00 0 1
-J00 00 00 0 i 0 @ 0 8.1 ?n ?n 40 ?n oz 0. 0 0
110 0 0 0 0 0 0 0
a 04n P- 4- : za Z;10, 1 oo o
C;)0 -4144 -0 4 ~ 0 -0 C
.'a-a.'noOW~~~~~~~~ 0Ofr 0Q# ft~~ an~0.P 0r -4 - 0PO V
.4~~~~m~ an P- 04' ~ 0 0 0 ~ 8 0 0- 0 .400 P- 0
14 'n .. c ca.. .. .. .. .. .. .. .. .. .
j~n ZO 0 0 0.00 0v0 00 1;0-'
ý "a o 0 0 1 00 Too zooC ONO 40 <a -
.•Y wo C) 10 11 42 0 0
C; 18'a4 -v -o440 -.4
]ýC-AD Rttaort No. 36;_A-80Z0 Oe j10 0! *ý 0 9 ' 0 .
1 00 0 000 000 00.0 000 ýOo0 a0 00 000 coo cooo4~~~4 *0 0 0 C 1; 90 .0 0 .0 .0 a0 C>l ~ .00 .000o 0 o40 0 0o 000 -00o c0 coo Ab 400 v.o ,-oK4- 000 00 oo11 0 UP 00 00 00 0001 000 000 0000 00V
~ 1. OO 0 0000 00cc 0 010 400 ý00000Co 000 000 0010 000 ~0 0 g ~
'6 0 U z o0 z o 00o 0z0 0 0 40 C;0 0 0: S 0 0 0 049 t20 0 020 00,O~ 0 0 00 010 00 4 0 00 ; 0 0 0
to t so 9000 0 '~~00 0 ,o0 00 00 c; c cc * * . ~~N1 0 00 400 000 000 Ro0 :00 000 000 001 0 000 000 00
.00 0 . 0 1 00 0.0 .0 ** 0 . 0 . 0 0 co .00 *00a~ 000 00 00 0 00 000 000 000 0S0 00 oo 000 Q 0is~0 00 00 00 00 00CI'00 00 00 00 00
cc, CI0 00 00 00 00 cc 00 ORO ~ ~I * I I * pi I I* 1* 1
6c0 coo 0000 00 00 00o coo a 000 00o o o: )416 311 40 Zo c. . '00 . c . a 0 a.o - a ¼,:!*I C; C
0 .0 *:20 .0 C 00 049 Cp 10 .Q via a00 00~ a0 V W ..) a 0 N>.y-0 ao 00 0400 a~ -'- V4 P-0 00 I> 0P00 QO 0 Q000o
40 0 0 00 00 00 00 00 0C 00 O c a10. It! 0ý a 0 10 00 1
00 Or cc a~ 0E0W WicO 4z C 0 z C C ýI I li I 1 0; 0* C3 ,a
009 1.41DO 00 :10 .m 0 .v'0 0e .00 .400 .. M40 - 'a'0 010 '40 *1~ go 'C1 .'0P .34 CO-~ Of ~ *~20L0 vr .-0 0n 0-. %m .:0 4w o N O a0 ~ "-j z 11 0 :0 0 ;4 0im. ^E Cho *Ov -0 a N 1 2 ;1 0 U. m0 *WO Q fca Va .0.0* 0 .040 .0 .0 .1 0 - 0
IK ~ ~ 010 0000 o 00 00 00o 00 (0,o Ca
=I. .9 . .F4 : 0 10 -0 P0 0 ft000 aa
00 00- t 0 ..e a dm '-w m v14 No- 0~c -W a E 0 0'b1 x 040 01 o 0 (4a4 ý09 Q oin 40 i a0 v v 0 -0 W -0 4:, '40 .0 -0 00 .0 .~ .0 coo I 4
A1 C. -.
U *Oj ~~0 .0 .0 ~ .10 1.0 .0 o .o *i 8 0
W, 00 0 00 00% V 0 00 w ý :.,. *00 0fm~~ ~ ~ 0 0 00 ow~ 00 0.04 3 d^O f
)w0 led. 400 a'4 goo 0(d'0 -40 404 1- mS 010 00 . r40 w hob .0-00 0,0 0.e. "a - 0 04
-0 0 as .0 .dft in0 1. 4 _0 00 400 -8 0 ý L41000 01 0 00" 00 0' 00 00 000 0
0i 0; 0 0, 0 0 0 0.- o a~: 0m0 cin wt a? 1-:: Clo 2
~0 -0*.0 M00-e4. 0.0 0.Q .*Q a n-v% I'
cc'E ttfini In Nýw(i 0 od n 10 (i " 1H 20 00 111 V -mm. me *1p. if0 -40 -0 cc0 .0 -0 04 0p 3 W o W
0C: 40~ 0. 40 0.i I V100 0.4,00 0-t 0- U o-:.~ -
U~ ~ 81 * .0 0 0c0 0 a4 0 040 0 ~0 440" Ii 0 0 0 0P 0 0 0- 021 1 .? C,- .0 a,0 001 0,0 0E~ 00 00" 0,0 0o0;ooo o o
'1-0 -:!a *-a -V0 V.` 0~ 0-o .400 .- Paoo ':m .0 a mo-o;0', Uil 0 a a a M'9 -00 000 Ot a0 I'Mt 4
on -ý t- 0 0 r/ -4006Best .a AaiIbi Co
HT:-AD Repork No. 369-A-8020 P~A4
to 46 *0 * 0 . 0 0 . 0 * 0j.0 .0
0; 040: 0 0,; a Z 0 0~ 0 0 0
loo; 0g 'go0 0 ~ 0040! 080 0l00 coo 00 00 0:I 000 P n 000
*0 a0, * C 00 .0 00 .00 ao .eo .o
C, 00 0 '0 0 ' 4 00 00Sl 0a0 00 00 00 00 003 0U ~ 411' 0l 0 00 00 00 00 00 00 000 000 000 00 o0 0
.i00 .0 .. 0 * .00 00 00 F_ 0.0 *00* 0g
1.0 .0 0 0 a 0 0
19 0 @00CCO 000 00 00 000 040 a CO 00 000 00 000 000
42 j jJ a 00! 80 a a 0 c o. .40 0o0 00 0-1 'o 00 0 0 a00o o0 00 0 .00 0i 0 Oa 0 0 0 0 0 C3 00 -4
CIO0 000 o00428 C? 8 10 Q 0 00 003 .q G
00~~c C0 0 00 '0 0 00 IO 4310
. 0 ! .4' .0 00 .PvO *04 0 400 4 .9o *0 *. C .40 co 0 -.
og0 coo!0 00 -w00 .000 -.700 000 Co ,CO .00 0 0 o c10 00: 0 a 0- 0 . 0 4;)
40 o 00 0coo ~ o 00 0 0 0 .
j03 ;0 jao 0e C;0 .80 .00 0 OOa04L IL 46 30000 0 C00 00 '040 400 -00 0 00 aO. 00 oo r
z li'%J -0 *oo N0o Coo 00o N1.0 @ 0 "0 0 00 6 ro 40P0 400 004.4J10 0 ýD * .0 .0 a: 00 -0 a 00 *.0 .0 V~ e.9
00 0 00 001 00 00 o 0 500 00 00 00 a -o. 00 00 N 0 00 C 0 0 o
a@0 0 .0 Co 0 40 0 @0 00 00 020l 00 C
0 .00 :Vi fm 01 34 C0 Of 0 V 0 a 0% a @
j c .4 0 .1`09 0 0-d 0 a' .Q5 '.01 *0 ~ .0 a 0 .NO0 cl 0 .1 CU
@0 00 100 0 0 .00 .0 0 0 0041 000 0 1 c; 1ý1 0o 0cc 0 ~ 0 0 0 .0
0 .4t 0 c c
.14 901 9140 :0 .0 40 *% 0 00 05I'O 0 *O .4.
-a o-0 * 0 40o 0 $ C0 NO~ 0540 -o05 Zra 0 P ou 1^ 4Sw 00 00 0~ 0I a .0 00 .
Ofz 0I0 0 00 0o0 0 010 03 0
4 029- ~1.00 00 0 9 9 00 7*.o 4;0 *- 'o 4* c; j .9- Z.0 Z 0 90 '908 -0j .90 .00 0
.;0 c0 .0 .0 .0a 0
-9-01 ~~ ~0 0 n0 v .na. S 0. .. o01* . . , 0 Oo 100 00 00 005m ý 0
V '0010 Z0 PO 0 0 0 mo 0 0 0 0 00 0 0 : 0
eý o 011000 oo 00o 1O ý000 040 0P0 .a0to 4 mo a... 0 *.0 .. 0 .. 0o .. 0 .. 10 *. . '8 .
0 050 040 ~)0 e0 0 Z40 o0 4 00 40 40 00 OVID0 0 400
0;C 0 0- 0 0 -
0 0 4D #0, f" 0 0 90 -0 0! 9 .^ US4r Ig ; o005 000. -4 IRS0 a-C 044.0 0 %o a IeeC
-w 1o' 10-0 00 0 00.8 , 000 00 0 3
it4*01ck 09-0@eSl :30 09- 90 0,'0 09-00 0,.0 0-00 09- 11!0 .0*4-U~ 09 .0c. 50 00 91.00030 09- 09- 040 00 09.0
1,; 9 40K50 04 040 0OCo 4010 040 0s; Oe 01 l .0 of a 01 0 c;0 0 9
1; 1 C; Is24 1
t;~ 4; c; 9-0 -. N
ep-~~~ 1i -00 00 -- t 4o - 0 ;4 - N'cOtAI, n0As0r,40 wcopyt 04 ".1 Wtw d t N
2ýrC -D Report No4 369-..A.8020C:. 0 1.0.0 o
to i V4 .08 .0 .0 00 .0 O *Oa0- CL
Ak 0
wZ. . 0. 0 00 a. 0.0 '0 0000o 0 0.0 01 000
01 :00 zoo 0o e~ oo c0000 000 000 -o 00
.10 .00 00 .0 001 .00 .0 0 0 80 r0 0W%0 0 0' z0c 00 0'U0 000 -0
POO~ g 0 C, .. c 0 P.- 0' .40 0 4600 WO 4.0 0 0
00a
__ 0100 00 Q 00, 0 0 0 000 0 0 0 000 O'00C
11C @0 0 10 0 000 00 000 40ý00 ;10 00 1000 000 u C 10000 g 8 g 0; #gs0 OCO vs'00 ~0 00 o
04Jo, 00 00 0 E0 00 0 0 0'0 Cal 00 :00 0 0 0
00 00 00 00 00 00 00 00 00 00 00 0.0 n0O i oc, 00 P 0 ,o aC
o* 0 '0 08 0170 00 00 `0 a ~ gg c 1 0
so 0~ soa0 0 : ý
'0 00 000 00o 0 ' 00 C o DI 0 -
0 ~o 00~00 00 oo: 0 00 a0 000 010 0 0og 0 00 co0.10 .0 0-0 00 .00, Oc <00 .00 .0 000 .00 0 C_
O.r .lc 11301 00 0 ZOO 0 00 090 0.0c 0 0 000 0'0 0 1000 0010 -40o.0
0c
UO 00 o' LO0 ~0 00i 0~ cc 0 00 00 :00 00 010 0
iz@0 00s-1 0') 00 00' @0 .0 00 00 o 0 ýO oC7 0 oo0 l
.0 00 00 00 '00 00 cp C 00
40 000 0 00 00 q0 p . 0 0: .00 0 o 0 0
C;,8.00
. - F CP 0 -01 00 C4f"0 OD 00 4 0 .410 01 0 40
q4 "a! .0 *o .0 .0 . 0 .o Q, .0 .00 :5 . .1
o A.0C&~J 10 0 00 0 00 00 00 00 0000 4 o0
1t 0 0'ciP 0 0 01 0 0 0 la 0 00 00 o o
C, I.40~~ a*o C,' o~i .00 00- *4~.o 00 .1%~uo *0 0
0 , .0 D 0 N0 0 1.~r0 .o . 0 .00 .
'0 0 -'* F -00 -0 - 0: '0i 0l 01 ' 0 '0 0 o
.4 00 .4100 ,fO D0 0 4-C0 o. a 40 0 c02~4 .t, 4444 (11N AD40 .0?4 O O 4 #0: , 00 CaO
U, 0910 0W 401 b ; 400 C 4D 000 ;cc
04; '0 o 4 40 40 .0* f
Le.00 A40! 600 .440 .10 *i .4 00 .~j0 -- o' 41F0 fn 0 MW0 N . 0 ýOr4 -. 4-0 0490 m- P.4. W 0 " 'o '
I ftP401A a I4 c C m0; m0, 4 t0 M 0.0! .04 0 v -0 0:0".c.._;0i
30)( 4V0 f~0 0140 fl0 ii~0 l'440 40 c 40 .0 'O 4140 C) 0 01 0 !A
ox .0 0 .0 100 oo 00
00 0 00 0 0; 0.00 000 0
10 .m 01* 4I
-10 MO; P.00 il *0 *O 40 .4 40 '0 .0 . 00.4a0 0VIA a "'o 0 ý 1-4 40 P-0440. Q,%n 0" V.l 04 1V0 1000 1-401 W 00
Do o!00 *I 0. 0, ;oo N40 .~0 1o 0. ., .O14 #0-. 00 ,wl 0
19 00 03 0 00 oI 0~ 400 400 -40 00 400 100 £10 1 00
-00 '. 40' 0 - . .0' .0*0 * 4. .0 .0 .0 .. 44
00 0000 0 e:000 0 00 00o 8000 0
"ol 0 13 0; 0 o 0 0- 00 0
S.1-4 0 4.00' 40 .~ 0 . 04o-00; .4o0 o. 0M o-o: O Wý gr -0 0 wfO 01 -4.00 we,
01 ~ W.4 0491 -0 %n * ' m4 0. -C (-- l a I 0 494 0 -~a r t
0. 10 a 4" 1.0 oN 0 ý S0 0 1 r4 01 -40 '-0 .4 0' -40 -4 n6
;o~~ .01 a 4r -t.pQi0!4 o n 41:0 on 90 0en 0 fm ofO fnO f"O lN 0it4 041. 'a'
0 . 00i 0P v L,40 0; 8. 4 0# o 41 0494O0 o4~ o 0: 0:
0 0 o; 0' ;
.10 0o .0.0. .: 09 0 9V 0 P 0 -NO .. 10. 0 i%0 0 00 00 0 010
.0: .C 1. .
!C; 40 4.0 04 4'' .Q4 a 04 .0I 44 .04 .04.
-~~~ ~ t
4 4 .*4 4 4 .
N 10 P- 0 0%ý0 0 n0 7.0
-A eotta.369-1 -8020 'Pge -LI t
01-
b.000 400 000 000 cc 00 o~c 00 .0o 400 000 0,-0 - 0g .0040 c0 000 0 t1 00 i 0040 0 0 00 a0 N 010o g0o f"0 o 0
DOO aJ §0 0 0oo a00 00 00 00 400 00 00 00 . 0040, 0 00 0 00 o 00 o 00 00 001 0 0 0 *
-A Oc Ova 00 00 00 o: 00o o0 000 .04-0.coo 0000 co 00 00 000 00o a* 0
00 0 00 00 00 c0 . 00 00 C3 00, 00 .00c 00 ~00 .
gg0 g c0g 00g c~ g0000 0000 000 000 000 a00 c 00 0 ;0 00 0 .00 '00. 00 *00 .00 go0 'ON0
99.0 00 90 0 00o Qoc P 00 00 00 00i 000 0000 0 0 0 0-4coc 0 coo0 o !00 600 60 0 8-
00 00 000 coo.
00; 00100 00 o00 001 '0.0 000 000 000 00ogo~' 0 000 00 .00 -00 .00 001: o Il . 6C6 0
.0L 00 80 00 00 00
.0 *0 oa *$10 ucto .IA 000 co 40;o 0.0 c0 c'oo .r.0 * 0 NOxUU S0 i 10N too~ 1,00 1400 to -00 40.3 00 F- 03 iD 0 a N
i uIt -o 0 0 0 6400 .Oo .00~ P-0 O00 .00 0'.'W~~:. 00t 00 . 0 0 . .00 *o; .Oct.0 .0o~ q 00 00 0 0 00o 00 a0 00 00,. 00 00o 0 00 .t
c0 of Q 0 :0 a-- 0
.0 ~d IV0 .00% .00 CI~o..~ .o . o .O; 0 ~ - r4. 0r.. j N 0 .1P0 mmo m 00 f..@ 0 0 a tt 0 IQ0 v041'- 'ON c4rlr'-0 P "o 0 a_jJ 4s 00 .- 004 P.n ~0Q 109 U 00 NO ""0 0N % ý -a Na 0 0ofn0 '40' 0 (V 0 6
00 .0 oo-m4. Q0 400 N O, .0 V_ NO 0' Nca0 'r o .40. 00 .401* 0 NO 90.0 8 . .0180. IC.; 10 .. 01 * 6.0 6.0* 0
00U a00 0 0' 0 00 00 00 00 .0 0 0i.4
#0 600 '440 * 9406. zI 6440A 0; N0 0. j
F9. *o *N 40 w .00 0NO .90 .'g a4 .0' NO-t. 0.0 0T9 NWO go 400 N-0 '0 .30 f40 0 (.fn0 NO .64-0 If%' -4.000 0' 60000 NOON fl. i0 N9- I 0 -6-40 _ 0 a0" .00 .tm 0 0 N0 CJ'0 I0 ,Ju
0 C 00 40 .0 0 00 000 0 0-4 00 0 000 a O 000 .009 0 0 w.~
0m 6 0 .00 . 0 4".0 -0 0 ZNO .0 "0 . 0 40 .00 0 0 00 00 00 Z0 00 00 00 00 0 0IL 0 f 0 .0 0 0i0 r4 9.1 f"
.9- W00 .0 *40 00 0 0 *C O
.0 a 0M 0 0 -0 0. 0 .. & N0 NO 'U - N 0 %O*VotN' U;o 'N'.J w-,40 UIl 0 r4 0
U 0 .0 40 0 k .)u 04. w tooj a 00 60 00 0 00 14'4,
*u 4 ) *0 60 6 00 -0 .0.0 Q~ 000 00 00 0 0. 00 0 00 0 00 0 0 0 .
ui 194 8 .
U 0 w.0 *0 F- a0 o -a m0~ .0 *C> .0' 0 a1
ki-4cw " 0 ýr0 'm 'T0 mC ena r0 0'nr0 fn 0 J'0 T0 j6o0 -7 04- 90.0 4'. c0 000 0 0 0 0 a0 0 0 00 00 0 00o 00 C
6' ) wo a' o
.9.~ 914 v0C .0 04116-o41 0 *0' Q, IjO ._U -.041 .' 0 1 0~F-.
00 '00 00 0 13 0 0 00 c 1 0 .0 ",IL.J - -a 69 '~~ ' - a O -'0 t 0 ,0 10 6 -_3 N- 0 ' 0
r4r 0.0Nc
L. x 0w 0. A c ' j C jj .-0 :3 6 01 .6. 643 o4u
.' L0 r: MA C! 6 01 N h o'C;
~~~~i0~~~~~- 0. O~ 14N 0' O' 'N .,4 ~ 0 0 ~ 0 0
MO'" ' 0"0 NO I -j . r.400 - 0
0-0 .4 o0. '0 . @0 n C.0 *' Z 4N* *N : -0 Too. 0*'- 004 (@4010040 C43( 0 90 40 '09 0040 10 0a 4 000 NO * 0 0 :"r 4.
, L) 0 1 1.1 1, jF I 6 ; 6 I~
~,u. 0n Y. 0 6 ' C
.fl-. ~ ~ ~ ~ es Avilbl Cop, 4 . - -- '5 . 4
11LU-Aij 1k%.epurt No. 531j-A-bU/,0 Page A-52
PITCHING MOMENT COEFFICIENT, Crl/c
(Tail Boom Support Strain Gage Balance Data)
RUN CONFIG. C/ RUN CONFIG. DATA CT RUN CONFIG. POINT S
2 FRBVHT 1 -3 .00161 9 FRBVH 16 -3 .002332 00202 17 .002073 i .00279 18 .002604 1 .00298 19 .002505 .- 8 .00339 20 .002826 00371 21 .00224
7 .:00408 22 .002788 -13 .00503 23 .000589 . .00439 24 .0031010 .00594 25 .00436
11 -3 .00208 26 .0024212 00255 27 .00231
13 1 .00270 28 .0021314 -13 .00630 29 .0025015 I 0061916 (00633 10 FRBVH 1 -3 .0021917 .00779 2 .0019418 -8 .00424 3 .0039819 .00545 4 .0019820 .00433 5 .0035721 .00362 6 .00581
7 -. 000093 FRBVHT 1 0 -. 00061 8 -. 00052
2 0 -. 00075 9 .001873 -3 .00132 10 .001154 00155. 1 . 000705 .00202 1z .002046 .00236 13 .002537 -8 . 00370 14 -3 .002038 | .00433 15 -1 .001399 .00485 16 -5 .0023910 .00551 17 -7 .0029511 -12 .00630 18 -9 .0049012 00693 :9 .00550
13 t .00755 I0.0050721 .00424
9 FRBVH 1 0 .00050 22 .003812 -9 .00447 23 .004613 .00422 24 .004424 .00368 25 .004685 . 00448 26 . 004806 .00495 27 .00495
7 .00425 28 .00451
8 .00449 29 .00671
9 .00441 30 .00899
10 .004/aP 31 .0040611 .004&7 t A ai - 32 0042912 -9 00429 ''v a C 0040913 -7 .00414 . 0045814 -5 .00449 . 0049915 -11 .00432 36 .00524
(continued next 37 . ,ý ?column) (continued next page)
[ %±0-%i.i tpurz 1*o. 401-A-duzu Page A-53
PITCHING MOMENT COEFFICIENT, C11/-1c
(Tail Boom Support Strain Gage Balance Data)RUN CONFIG. / RUN CONFIG. DATA C /a
RN .POINT S m POINT s
10 38 -7 .00418 12 FRBV1H 1 -3.3 .0011839 - .0522 1 00157
40 -11 .00422 3 .0016941 -9 .00447 4 .00176
5 .0020811 FRBVH -8.3 .00423 61 00206
2 .00534 7 .001503 .00768 8 .001474 .00293 9 -3.3 .002335 .00107 10 -1 .002876 .00412 11 -5.3 .001657 .00402 12 -6.3 .001598 .00414 13 -3.3 .002249 .00402
v 10 ,. 00432 13 FRBVH 1 -3 .0021311 .00411 2 .002101z .00221 3 .0042713 .00030 4 .0010914 .00690 5 .00007
s15 .00953 6 .0022316 .00387 ? .0003717 .00349 8 -. 0010818 .00149 9 .0031319 .00432 10 .0051320 .00493 11 .0018321 -8.3 .00424 12 .0014922 -6 .00451 13 .0012423 -3.8 .00573 14 .00224
24 -8.3 . 00416 15 .0026225 -2.6 .00185 16 -3 ,0023226 / 00446 17 0 .0021727 .00306 18 -5 .00226
L 28 .00152 19 -7 .0022029 -3 -. 00044 20 -9 .00244
I.30 .00074 21 .0051331 .00198 22 .00539
32 .00343 23 .00353
33 .00498 24 .00235
34 .00686 25 .0036935 .00221 26 .0024436 .00362 27 .0008037 .00055 28 .0057838 -. 00016 29 .0077339 .00197 30 .0042640 .0011041 .0004742 . 0022943 .00275
44 -3 00194
nVi..-AUi Auport rio. 50-A-dUZQ~ I-age A.54
PITCHING MOMENT COEFFICIENT, Ct/oj
.(Tail Boom Support Strain Gage Balance Data)
RUN CONFIG. DATA C Cm/r RUN CONFIG. DATA CPOINT S m POINT S m
14 FRBV 1 -3 -. 00239 15 FRB 1 -3 -. 001032 -5 .00281 2 -3 -. 00165
-3 -7 -. 00332 3 -4 -. 002314 0 -. 00124 45 -3 -. 00139 5 -1.8 -. 001086 r3 -.00182 6 -0.8 .000367 -3 .00023 7 -2.6 -. 001878 -9 -. 00160 8 -3.5 -. 00267i• 9 -11 -.00234 9 -1 -. 0002010 -7 -. 00117 1 -. 0211 -6 -. 00074 16 FRB 1 0 ---12 -9 '.00168 213 -9 -.00286 3 A14 -11 -. o00371 415 -7 -. 061875 -2.6 -. 0022616 -5 r..00068 6 -3.3 -. 0026117 -9 -. 00282 7 -1.5 -. 0010418 -3 -. 00128 8 -4 -. 0034519 -5 -. 00226 9 -4 -. 0030720 -7 -. 00316 10 -6 -. 0045221 -1 -. 00057 11 -2.6 -. 0018422 -3 -. 0014523 -. 00224 17 FRB 1 0 ---24 -. 00021 2 -3 ---25 -. 00408 3 0024426 -3 .00158 4 -.0030027 -4 -. 00229- -. 0032128 -2 -. 00074 6 -. 0018529 -6 -. 00368 7 0010530 -4 -,00230 8 -. 0025431 -. 0028732
3 .00298 18 FRB 1 0 -. 0007334 -. 00481 2 0 -. 0006035 -8.7 -. 00488 3 -4.5 -. 0042836 -10. 4 -. 00591 4 -4.5 -. 0040537 -6.4 -. 00354 5 -6. Z -. 0045038 -4 -. 00257 6 -7 -. 0046939 00-.o14440 0003141 -4 .0030442 -3 -. 0024843 I -0051744 +. 0004945 -. 00231
- -.- .. ..* . .
1 I III -
HTC-AD Report No. 369-A-8020 Page A-55
PITCHING MOMENT COEFFICIENT, Cm/a and Cm*
(Tail Boom Support Strain Gage Balance Data)
RU ONI.DATA DATARU CNFG.POINT ~S C/Ma RUN CONFIG. POINT S Crn
19 FR 1 0 -.00047 20 FRV 1 -3 .01772 -3 -00079 2 -5 -03523 -6 -. 00150 3 -10 -.05754 -8 -00155 4 -7 -. 0447Si5 -10 -. 00191 5 -5 -. 03456 -12 -00209 6 -3 -02237 -13 -00223 7 0 -.00648 0 -00013 8 3 .01419 0 .00061 9 -13 -.060010 -3 .0 0175 10 -11 -059711 -5.3 -00272 11 -9 -.044912 -8.4 .00367 12 -7 -.037913 -10 -00423 13 -5 -.029914 0 -00065 14 -3 -u16915 0 -00094 15 0 -002916 -2.6 -00252 16 3 .019117 -5. 7 -. 0039318 -8.2 -00513 21 FRVH 1 3 -.083419 -10 -. 00576 2 0 -.054720 0 -00056 3 -3 -034921 0 -00078 4 -5 -.0194
5 -7 -00066 -9 .02517 -11 .05318 -13 .0761
9 3 .072510 0 .052811 -3 -. 0379
-5 -5 022813 -7 -.06314 -10 .0264
HuGI4E TooL. COMPANY-AIRCRAFT DIVISMo 369-A-3020DEL REPORT NO. PAGE51
rNALYSI iis a
Mwe mein roo safour-bladed, fully articulated system havin~g a load-
lag hinge located 16.19 Inches from the CL~ of rotation and a flapping and
feethering hinge located 5.50 inches from the rkof rotation. Centrifugal
fore* to transmitted from the blade through the lead- log hinge to the out-
boasd end of a pack of thin stainless steel straps and is reacted by the cen-
trifugal ferce of the opposite blade, so that the hub is not relied an to carry
the centrifugal fore*. The inherent flexibility of the laminated strap peeks
permits flapping and pitching motions to be aoccdmated by stmuctural deforms-
tumrns. fts flapping and feathering hinge serves primerily as an qlipsit
(j point; a self-lubricated spherical bearing free to slide on a pin proides
fre~edm for all angular notions and permits elongation of the straps due to
centrifugal forces
The straps we of high strength stainless steel strips with taflon
sheats between the laminations to prevent fretting. The hub is a premium
strength alumimn alloy cotig, smonted on tapered roller bearing@ Wbich
transmit throst and hub moiants to the mast. A six-inch radius curved
surface (shoe) is provided to permit vrapping of the straps due to ftipping
and pitching motions.
The blade is a composite structure consisting of: 2024-T4 alumainum
extruded spars* 2024-T3 aluminumi skin, 2024-T3 aluminum channel, 2024-13
aluminum strip, and extruded braom weight at the leading edge. All these
parts are bonded together. At tha blade tip, a bronxe weight is bonded and
riveted to the blade. At the root of the blade, the upper and lower root
fittings are banded and bolted to the blade. At this location, the blade
HuGHES TOOm CAMPANY.AIRCRAFT DIVISION 369-A.8o2o P' NAylMMODE L REPORT No, PAGEi 5-
AMNAMYIS IY, •'n mi tests of an op~ertioal O-G
CHECKED 9y V. y* Naltaipter in the Amo 401 1 80' vied Tmnel
base reinforcement f~row the 2024-T3 aluminum doublers A 2014-26 aluminum
forging is attached to the rost of the blade for takiug the doger am bed.
Mhe blade bea -8e twist and no taper. Figueo Wl5 presents significnt blade
di etn ams, the flprise inertia, and the cbhrdvi inertia.
The blade hea an N&CA 0015 airfoil sNation of 6.83 Inch chord. With
the traTlmng edge ezteunlon the overall chord to 7.21 Inches. Figures D.2,
-3, -4 present the opeavise dist•eibution of wtGiht, choridvise e.. location,
and chordftNs mamnt. Table 3-1 presents a summary of the Rotor Xmai
p"Oparttese.
The main roter hub controls are illuetreted In Fig. 53-. C•ycli end
solleetite pitch notions of the rotating aoshplaee are carried to the integral
boma on the pitch housings by short links with rod end bearing@. The
rotating suesbplato is driven by links fastened to the hub. The rotating
oashplate is connected to the non-rotating ehsbplsto through a double
row bell bearing. The outer race of this bearing is a pert of the rotating
ubVsplete; the inner race is a part of the non-rotating sudhplote. The non-
rotating seshplats tilts on a self-lubricated bearing surface mvingt
against a hard sorfece on the main rotor lost. Rotation of the non-rotating
weshplate is prevented by one of the links that transmit conteol motion
from the mixer assembly.
i4
!uGHEs TOOL COMPANY-AIRCRAFT DivisION 369-A-8020
MODEL REPORT NO. PAcE B-3AN•ALYSIS,P*PAJ BY R. IcaLtert Arodynawic Tests ef an Operation1 lH-6ACHCKEo g 5. V. Jl eHe-licopter in the Amos 401 1 80' Wind Tvmae
TAUK 3- 1
IUBARY - RCTR0 MASS P3.tg
RENWAUX LEAD- AG FLAUTING
U113I Lbs. 26.96 28.61 37.25
oEMr or GAVITYPitch Axis (.25C) In. 0.03 0.04 0.21Loading Edge In. 11.74 1.75 1.91Ce•ter Line of Rotation In. 80.53 76.85 61.74Vfrst Mment Lb.-In. 2171 2199 2300
NONT Of MEMAcr ABOUTr
Center 1-1 iotat & .25C Lb-In.Sq. 239883. 241256.S1-1t.8q. 51.78 52.07
lo-L Hinge & .25C b-In.Sq. -176192.(Sts 16.19) 81-Ft.sq. 38.03
Flop Hinge & .25C Lb-In.Sq. 217083.($t1 5.50) $l-Ft.sq. 46.84
Pitch Axis (.25C) Lb-In.Sq. 9q.72 173.33S1-Ft.Sq. .0215 .0374
7lap~ping 1b- In. Sq. 64529. 70865. 99162.$1-1t. Sq. 13.93 15.30 21.40
]riteting Lb-In.Sq. 94.42 98.24 170.6331-l•.sq&, .0204 .0212 .0368
Load-Lag Lb-In.Sq. 64582. 70919. "269.S1-Pt.Sq. 13.94 15.31 21.43
PRODUCT OF INERTIAAbout Center of Rotat Lb-In.Sq. -73. -65. 10.& .25 Chord wLL 1735
ITE14 WEIH L .ZC-I O
ROTAT'IG HUB & RETENTION ITEMS 29.00 464.FRA4 HUB CENTER LINE TO FLAP HINGE
1Z - W(R SQs), R - 4.00 IN
1Z - 29.00 ( 16.00) - 464. Lb-In Sq
Y. FLAPPING BLA2'S 149.01 965025.WT - 37.25 X 4. - 149.01 LbsIZ - 241256. X 4. - 965025. Lb-In Sqd
TOTAL ROTOR GROUP 178.01 965489.(208.39 SI-Ft Sq)
Wnizht Ybtýun of Inertia About Rotor Centerlir~e B• ~Best Available; C o r
Hum= ToOm COMPANY-AIRCRAFr DivisIO 369.A-8o2oANALYSW M EEPORT NO. PAGE '-4
PREPARED mV 1. Is st*rt Aerodynamic Tesct of an Operational OI-6AtMCKIDU my 8. V.a. _Helicopter In the Amos 40' X 80' Wind Tume
.17.19
1 19.19
~~.i- 23.62 .3737 5.570
26.19 .177 53)60
"- 36.19 .1136 3.276
- 137.625
1 10. osX 10 lbm/1n2 1G3 -..
h~u16.1
TTT~~ ~ ~ L j. 1- -
7 r~-1~~ i
41 I 4
7.A.I ~ 1
S~t=¶~ r~ L ~ 1 1r
Lf
q . ............ I
4 .1JL*
L 4
-t -i , I
I
In
U U.
A .E A . 1
it .. d .
-I-
vlr~0
.. -__ _ _ _ _ .. .
to.1 4 . .. 4 I Q . --. I
i..i
---- 4 --4 --1" 1t -I-6 -L.--V -r-
4, -4 7 -T .
-- II~7,71-7717I
if RTC-AD Repoit No. 36--82 page B-8
0
