NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
JOHNSON SPACE CENTER _diTd a]dl_lagement xrvlcn
HOUSTON, TEXAS _ ram°" 0 __
I
1977013202
https://ntrs.nasa.gov/search.jsp?R=19770013202 2019-01-24T13:56:07+00:00Z
@
_- March 1977
_T
_ DMS-DR-2184 "
NASA CR-151,061. :
_ TRANSONIC CONTROL EFFECTIVENESS FOR FULL AND
_ PARTIAL SPAN ELEVON CONFIGURATIONS ON A 0.0165
_ SCALE MODEL SPACE SHUTTLE ORBITER TESTED IN THE
il LaRC 8-FOOT TRANSONIC PRESSURE TUNNEL (LAb8)
y
g
_! Prepared under NASA Contract Number NAS9-132_7_4
i, Data Management Services_ Chrysler Corporation Michoud Defense-Space Division_ New Orleans, La. 70189
:__ for
Engineering Anal_sis Division
Johnson Space CenterNational Aeronautice and Space Administration
_:, Houston, Texas
1977013202-002
/
3:rINDTUNNEL T_,_2CI_CIFIC_:
Test Humbers: L%RC 8' TPT gSO• _ASA Series _Tumbers: LA4_
Model IIl,_,er: O89B-139{Te_t D'.te_: April io %h-o_,Gb17, 197_Occup_%nc:_ri[o_rs: _8
FACILYTY CO0]LD_,!ATO_,:
Be_..r< Spencer, Jr,; Langley l{esearcbCen+,e_"
Mall Stop 365Langley f-_'t_tion
. IIa_pton,Vir[:in__. ,"3_g5
Phone: (_04) 827-3911
PROJT,CT ENGINEI_:
Bernard Spencer, Jr. George WareL-m_ley Research Center Langley Research CenterMail Stop _65 Mail Stop 395L_ngley Station Langley StationH_mpton, Virginln _3665 Hampton, Virginia 23665
Phone: (80_) 8P7-3911 Phone: (8Oh) 827-3911
_ATA MANAGEM_'NTSEINIC_S:
Prelo-re,?.%_".,.Li_.i_on--J.W. BallOrer_tinns--MauriceMoser, Jr.
Rev_m_-d by: G. G. McDonald
"_D._%n Ope._[on, _n.ta,V._n,-.ceL_entSe_vlees
Chrysler Corporation Michoud Defense-Space Division assumes no responsi-
bility for the data presented other than display characteristics.
_GINA_ PAGE IS |_ ooaQVAuw ' "
J
1977013202-003
, TRA_ONIC CO_'ROL E_F3CTI_EN_.SS FOR I_JTLAND
PARTIAL SP_,NEI_"_ON CONFIGURATIONS ON A 0.016.5
S_IZ. MODEL SP?CE SHU_2_E OV4]ITER T_._fED IN THEi
- L_RC 8-FOOT TRA_O_TYC PPSCSURE TUNNEL (LA48)
[
ABSTRACT ..
An experimental Investigation has been eonduete_ in the NASA-
Langley Research Center P-Foot Transonic Prensure Tnnnel on an enr_..
version of the sp%ee shuttle orbiter (de_ign_ted OqgB-139) O.Olg5 se,le
model to system_tieally detemine bo£h longitudin_l and l_teral control
< effectiveness associated _71th various eombin,_tions of inboard, outboard,
and 15,ii span win_ trailing edge controls. This report presents rem?It_}
from transonic i_l,.estigatlonsconducted from April lO through 15, 197k. 'J
The test _as conducted over a Maeh number range from O.g to 1.08 at
angles of attack from -2° to P3° at 0° sideslip.
$
f
J
1977013202-004
I I
Ill
£: TABL_ OF CONTENTS
Page
ABSTRACT iii
INDEX OF MODEL FIGURES 2
INDEX OF DATA FIGURES 3
NOMENCLATURE 5
I_I_ODUCTI ON 8
CONFIGURATIONS INVESTIGATED 9
TEST CONDITIONS i0
TEST FACILITY DESCRIPTION ii
DATA REDUCTION 12
REFERENCES 13
TABLE8
I. TEST CONDITIONS 14
II. DATA SET/RUN NUMBER COLLATION 8UMMARY 15
• III. MODEL DIMENSIONAL DATA 16
• FIGURES
i MODEL 23DATA 29
APPENDIX
TABULATED SOURCE DATA
O
1977013202-005
1977013202-006
ORIGINALPAGgm 3
- + + ]
1977013202-007
L
It
/
I%m._.OF DATA FIGVRES (Conel1_4ed)
SC_EDUI_ OF CO_,FFICIE_S:
(A): CL,CU_,c% _/D.,er,u. AU_
(D): CY, CTN, CBL versus ALPHAE
(E): CBL, CI_,',_ versus %LV-LO an(]DCBLDA:DT_TD_, DCY/DA ,,erstlsALPIM
(F): DeBT/A,D._WDA,DCY/DAversusATPNA
(G): DC%_qDE, DCLMD_, DCMI/F versus MACH
1977013202-008
/
N(24_;CLATJRE
_p General
SYMPOL _,_!_:-_,i0lq__.____C DD'I_ITION
_° a ._p_ed of sound; _/_c, ft/sec\
Cp CP pres'_re coefClclent; (Pl - Pm)/q
_ H MACH M_ch number; V/a
_ /m2,_ p pressure; N p-_f :
__ q Q(NSM) dynamic pressure; l12p_, I'II_ 2, psf
LRN/r. RN/L unit Reynolds number; per _, per ft
_ V velocity; m/sec, ft/sec '
O ALPHA angle of attack, degrees
, _ BETA angle of sideslip, degrees
PSI eagle of ysv, degrees
• PHI angle of roll, degrees
"_' mBss density; kg/m 3, slugs/Ft3
Reference & C.G. Definitions
Ab. base area; m2, ft2
b _qEF ring span or reference _psn; m, ftb/2 wing semi-spane.g. center of gravity
_REP XREF reference length or ring mesn_, verod_amlc chord; m, ft
S S_F _lng area or reference sre_; m2, ft 2
MRP moment reference point
_4RP moment reference point cn X axis
moment reference point on Y axisj"
_4RP moment reference point on Z exls
_, b base1 local
__ s static condltion_
i _ total condl tAonsF:ee stre.m ,
oRICINAL PAGF,I_ov v oa
1977013202-009
] ! •L= [ , lit "/
I;O_CLAT/_E (Continued) -]
Body-AxlzSystem
S_BOL _)NIC DEFiNiTION
CN CN normal-force coefficient; norm_lqsfOrce
CA CA axlal-forcecoefficient;axial forceqS ..
Cy CY side-force coefficient; side forceqS
CAb CAB base-force coefficient; baSeqsfOrce-Ab(_ -p®)lqs
CAf CAF forebody ny.tsl force coefficient, CA - CAb
Cm CTM pitching-i_ent coefficient; _ltchin_ e_e, n_qstn_
Cn CYN yevlng-momentcoefficient;yuvingmomentqSb
' Cl CBL rolling-moment coefficient; roll, ing momentqSb
Stebilit_-Axi_System
CL CL lift cocff!clent; liftqS
CD CD drag coefficient; dragqS
CDb CI_B base-drag coefficient; baSeqsdrO_
% CDF forebody drag coefficient:CD - CDb
Cy CT side-force coefficient; side forceaS
Cm CLM pitching-moment coefficient; pitchin_ m_ent_sln_
Cn CL_ yawing-moment coefficient; ,_winl_ momentq_b
C_ CSL rollinS.moment coefficient;rollin_ _omentqGb
I_D _D lit_-_o-dra_ ratio; C_C D
L/_r L/_ lift to f_.ebo_ dr_gretio; cL/c_6SB SPDILqI( speed brake deflection angle, deg.
6
1977013202-010
F'F._.¢L ...... ' -"...... _,,I±., D_'T'I'_;P ZO'T
_D_ ,_) fP_ _Imp,: o" O*....., ,'o__,.f_'_ o._ent ,r. eL_',,_n - ..,I
'"CT ;_T'CT_e ...._j .,,, ,_lop," rf lift cneff_rin,._t-;_, e!_,,on _._._lee- ----
t_,_ ,,, e.,y_,_; dCL/;_e, pe_ /,,,tree
OL_ DC?.T,DA :,lope o_ roll/of; '_omeut c-._rrlc_,:,_t,'_,.
_ile-'o'_<le_ler+._.or.c':--.'_,IC_/OB_, 9r'"degree
CruSe _CI&_E ._loI,e or pitul,ln_ moment ,'oopf!rlent ",s.
C-[_ D_/DA Slope of side ._rce eoe_fi-.ient ,,n."_.leror_
,;efl;etlo: euI-.'e,dc/n_,%, per _'ec-_.e
C_._ D,._/q._% Slope o" yn_:[:,C _r,ouent coe"_!clent .,s..._le-on;_e._lectloncu_",n, ,_(,v/r _ ., l_er Oe_e_
_a .%TL",OI: Aileron deflection ._m_.le;clevon _efl_.ct_on
For roll control, (_eL - _e_)/_, po_-Ctlve
r_efleetlon leOf.panel trailing e:l_._own
_e ET_ _lev_tor _.eFlectlon nn_le; elevon fle;leetiop
fO_ piteh control (_eL �_eR)/_, po_,tlve
. deflection trnilln_ edge dmcn
_#Lc VLV-_) Le._.m,t_o_rd elf,on panel deelee_,io._ de_ees
8eli ":LV-L! LefU6 ir,_o_trrlelevon p_mel deele_t_on, _e_'-e-8
_e21 ,_LV-I-'I _Ight _n_,o,._dele,,onpanel (_eflee£1on, _er.rees
_2o _LV-RO Right o.,t_o._@._le-on p_nc I flefleet_on,de_,-ees
Cm_ I D_41_R _lo_e of pitehln_c moment eoeef.ie_ent versusin_o..r.4elevon Ae'l-_%ion en_ve, i_._ de_ee
I_._.._Z/_ R.atloo" the slog.es of the In_o.r_ -levon
p_tehln:: moment cu_-e OVe_ the ._,IIspnn i
_BF BDFLAP bod_ flap deflection a_e, deg.
_'i_l(;I_'_, ,.- 7: ,_, 2L""_*'AGEm
0 "" *x_OaQUA_ ii
)
1977013202-011
t
1977013202-012
CONFIGURATIONS INVESTIGATED
The configuration tested was a 0.0165 scale model of a blend of
Rockwell International shuttle configurations consisting of a 089B con-
figuration with a 139B configuration nose forward of fuselage station
500. A sketch and photographs of the model are shown i_ figures 2 and 3,
respectively. Body base flap was fixed at 0° deflection.
Elevon controls were split at 0.60 b/2 giving the inboard and out-
board segments approximately 53 percent and 47 percent of the total
elevon area, respectively. The surfaces could be deflected in unison or
as individual panels. Maximum range of deflection for each panel was
from 0° to -_0 °. Combinations tested included: for pitch control,
inboards only, outboards only and full span l for roll control, outboards
only with full span and inboard deflected for pitch control.
To expedite testing, the elevons were remotely controlled by four
internal electric motors (see fig. 2c).
A complete description of model dimensional data is given in Table
llI.
1977013202-013
I
J
TE,_T gONDITIONE
T'_e mo,!el,^,zssting snpporf,e_ wlth aerod.y_.m_.cWowces _nd momerts
he-sure,_,%y ._ internal].,"too,rated six-component st_.%ingnge _al_nee.
Model an<Is of _tt_.ekw_-sv_r_erl from _.l_out._o to nn _e,mh _s _30 _or
_ %r._l?o_ _."_.nlipof O°. 1_e_olds 1_mhe_ _._n constant n.t a nomln_l
3.0 :."I0g p-.c_oot. Angle of ,%tt.-,ehh,_sBeen _o.'_-eete_1fo_ :lefleet_on
.o" the _.t!-__n,"bn]ancc ,mde_ ] "_d.
T;-...nz;itlo-ztr_pc 0.O_ 3 inch ,_J,l_compo_ _ of _To.I_O snm_ C-lt
,-_.o.,_..!OC_C_: I.C ..": _ft o"._the apex o_ t':c Cuno]_e -ridO.5 [nell
(mea.ml'e_i_t]'._-,u_;ise)."'tof the _'Incn_,",e_llct -_I"_"e_,Ic_l t_,._l
_._'_,,b,_,15"O'"_.G_.lqtC. bemoan...._'epvczen_ r,."'o.,.,--,""c, ._n#.ilrtue_sx,r(-"
i:..-_it:::'v-or,'e,:t_.,l?Or t a.se 9,',.-.smn'e,:,r2cets.
i
1977013202-014
G
TE,_TFACILITY DESCRIPTION
I_SA/L_ngley Rese.._chCeuter 8-Foot Tr_nsonlc Pressure T_nmel is
an air-medium fncility c&p_ble of _ttaining contin,.ouslyvariable Mach
numbers from 0.P0 to I.B0. It is a single-ret_m, clo_ed-c_rc_Jittunnel,
h_viug controlled stagnation temper_trre,total p_essure, and _ew-point "
tempergture. The test section is 7.1 feet sq_are. Reynolds n_ubers are
variable from 0.30 :',I0g net foot to T.00 x I0'_,-f_ependingon _ch
r_um__L _ud tunnel tot_l pressure limitations. Models are su_o_te_ in
the test section by a sting-sector system, b11tw_ll-mo_mting is pO,"ni_le..
Schlieren photography is _v_il_ble for f!o_zon_ shock-x_avestudies.
11
1977013202-015
DATA REDUCTION
Data are _ecorded st the _acility and reduced off-llne at the LaRC
Comlx,tation Center. Longitudinal dat_ awe refe_-ed to the stability-
axis system end lateral-alrectioual data are referred to the bodjf-axls
; system. All coefficients are normalized with respect to the projected
wing area (excluding the fillet), mean aerodynamic ohord or span, whichJ
_]_F = win_ projected nrea = 0.732 Ft.2
LREF = w_ng mean aerodynamic chord = 7._3_ in.
BEEF = win_ span = ]5._5 in.
All data _re presented alon_ a set of body and stability axes (Fi_re I)
passing thrm_gh the eztim_ted foE_ar#' center of gravity located _t a
full scale fusel._.gestation of i076.48 in. or 6U% of the actual bo_.v
length.
Eleven and aileron derlvntive dnta were computer-F.enerate(1by the
Chrysler DATAMAN-SADSAC Pro_r,.m an4 represent the loc,_lnlope of the
coefficient v_. control ,_.flection at ench value of angle of _ttac1,,.
1977013202-016
_, REFERENCE
i i. DMS-DR-2182, "SUPERSONIC CONTROL EFFECTIVENESS FOR FULL AND PARTIAL :
SPAN ELEVON CONFIGURATIONS ON A 0.0165 SCALE MODEL SPACE SHUTTLE
ORBITER TESTED IN THE Ls.RCUNITARY PLAN WIND TUNNEL (LAb9) ."
I_ 13
1977013202-017
T _,BT.P,I
TEST : D;..T."'_" T_ _20 (T._$,A)] DATEi "-l'"'7" -1TESTCONDITIONS
REYNOLDSNUMBER DYNAMICPRESSURE iTAGNATIONTEMPE,_ATURE
MACHNUMBER (per foot ) (pound$/sq.inch) (delPeesFaMeflhe,t), , ,,,;,
0.60 o _ InO, ._7 x 106 _.17
0.90 P.82 _ 20_ 7.P_*<
..,, × I0' 3.h2,/,
f_n.?o r._8x zo ;.'to
<
o.OP. J.00 -,.In _,.'_T'_
o.95 $.nl_x lo 3.9o
O.9q $.07 x ]0_ ;_.0]I.
_.n_ 3.14 x i0 .;.
i •
i
BALANCEUTILIZED: TIT?7-100 l
COEFFICIENTCAPACITY: ACCURACY: TOLERANCE:
NF _00 I_. _,, 2.0 i_,.F
SF _on I_. - I.._I_,. , ii
-I
AF in()lb. , ..; m,_;lb.
PM _;00!u.-I_ ,,,
+ _]_ ....RM ;iO0in..Ib .._2._,9_'_- "4
COMMENIS:
1977013202-018
H
la4
_4
1977013202-019
d_.MAII.T.,GBODY ,"m,_" __.IT O _ _ ._. ., ,,, , I ,,I500 T_ROMI,TARVL70-O0009._.
MODEL_CALR 0.0]._5
DRAWING NUMBER' VL_'nnOOn_3, VLTO=OOOI39B
DIMENSIONS' FULL SCALE MODEL SCALE
L ength 1990.3 IiL 2I.,".'2,0 IN._ i i| #
_=x Width ?¢_.0 I_.37_ TN.
,_:x Depth _48.0 I_.09_ _;;.
Fineness Ratio h._r 9 h. _d'? ]';.i |, ,, .......
A:_._ 1,_.))000 _.I_.. ,,,,1""_9-_7_r .,.
Max. Cross-Sectional ......
Planform ,, ,
Wetted .....
Base ....
1977013202-020
C _ADT,Z Ill (Coutluued)
( __. I ,4ODEL DIMENSIONAL DATA ,_:
UODEL COMPONENT : LED" ?_,'.P-FI_
i GSI'IERALDESCRIPTION. o0'_9_,-I._9
DRAWING NUMBER' _ "']','"n-nnO')?IrA
DIMENSIONS : FULL SCALE MODEL SCALE
Length _J_.'TOO 1...3'.)# .a p
M:x Width P_;'_,OnO ',. _7_
,v.:x Depth 91,000 .3hg
I.
r_eness Ratio ....
A:.-G ....
Max. Cross-Sectional ........... ''
Planfor:n , l h_.r-l;O(" _.'gPl,
Wetted ......
Base 38.%60 I._151H , ± ,,
ORIGINMjPAGE IS '_OF, ooR.quE
17
1977013202-021
I
f
: :",:;Lq ZII (Contin_md)
!.!ODELDIMENSIONALDATA J
t,,.,. - rl!,,rI_,.oo__CO;,IPONENT:0';'" '"" _'
u"="z'=_,,.,,,,_'"DESCRIPTION .Ff, _-_:;'
I_9DEL qCAL_.I: O.al/"
DRAWING NUMBER' VT,TO-OqO0911 ,.
; DIMENSIONS: FULL SCALE MODEL SCALE
L ength ,_l_6.000 _5.70 ° .
N:x Width i08.00,0 . I,,_
• _ :x Depth ll_.800 .I,.873
m_eness Ratio , , -[ ,-
p
: _:.ea ' i i
M C S ti Jax. ross- ec ana .......
Planfor,'_ ....
Wetted .....
1977013202-022
_,,,,T,I__II (Contfn,+-d)
- ',",';DEL DI,MENSIONAL DATA
i':.:!. CO_,+PO,MENT ..... '._... _T,_,.rO:' (f-ir, rh GAP) +:!_3
"=".-kAL DESCRIPTi_; Co ,__+.,','"+ti_,_ 1.;_OA,/BOrbiter el.:vor,,
;'0T11:E43 _ _ "i°'-"_ _'cr_*o_of Egg. D_•ta_re for one ri_e.
DRAWING NUNBER , _
DIMENSIONS FULL SCALE MODEL SCALE
:' Area - Pt 2 PI.O.O ¢'.0; :,."='_
: Span (equivalent). In. -_ "- "''!
Inb'd equivalent chord " In. 1-1g.O01_ 1-9 I_7 ,,
++ Outed equi.vale.ntchord/ total 55,192 0.9108__ i ||
} Ratio movablesurface chord/total surface chord ' -
At Inb'd equiv, chord ,0o_O9g..... O.P30_ .
At Outb'd equiv, chord o'h'-O0+_.... O'P_!_OI_
; SweepBack Angles, degrees ...... -
o.O0 0.00Leading Edge - ,
-I0.0.;: Troil,ng E+l_e -10.05g _"
:' 0.00 0.00Hingelin_ ....
Are+:Moment(N.r,n,.l to hinge line) 158"/'._.'; o.o071__.. .
t we-,,_,ro_-._ c_o_ 1_1,t_. _ +. .....
1977013202-023
r.._,_T;",III (Continued)
MODEL DIMENSIONAL DATA l
MODEL COMPONENT T,T_':r_: .c5 .....
GENERAL DESCRIPTION r':y'7,IG'riC%T_O',[_",R LTI._,r, VLVO-O00095.i i i i • im m|l
i i i
:;OD:;LnCAL7: o.01_5
DRAWINGNUMBER VL"fO..O00095--, , = i,
DIMENSIONS FULL SCALE MODEL SCALE
Area I0".380 SQ.!_. .o_9n nq._T.I llmm j
Span (equivalent) 201.00 ,,, IN. 3.3_,,, , .'[".
Inb'd equsvolentchord 91.585 ,, .,IN' l._I I;:.
Outb'd equivalent chord 50.83.] IN. .,°4 , IT'.
Ratio movablesurfacechord/total surface chord .............
At Inb'd equiv, chord .Z_OO .)_00ii a I
At Outb'd equiv, chord .400 .hCf)
Sweep Back Angles. degrees .....
Leading Edge _1_;83 _!+,.,_':t D"C,.
Tro,l,ng Edge _t, _p, . p_.P_ D-'G.
H,ngeline 2_.8_ ,34.,q_ D_O.
Area Moment(Normnl to hinge line) 52_.]250 CtT.I:T.,.4.O8hO C'j.L':.
zo J+
i "!.
1977013202-024
'_ TAF.T_F,I.Yv !qo,ltim_ed)
( I MODELDIMENSIONALDATA
V :TTICAL TAI5 -_. MODEL COMPONENT :. _ v_
: GENERAL DESCRIPTION i:.c'_'_Rr'I_.V' "v':_3TICALTAI'LDOI_L._W_ ATi_97T,_ i _
: 'qTIiEON.IDTT9U_,'DY;TGETX_7.
, i i Ill I | I,
_:ODELSC?.L2: 0.CIK5, ,, ,, -- _
"rr2_-00_09_DRAWINGNUMBER _ L ........
DIMENSIONS FULL SCALE MODELSCALE
Area 413.7500 PQ.}T. 16._CII _.I;.
Span (equ,valent) 315.7_ 5._I T I.• i
Inb'd equivalent chard _8._O I'+I. h.h,3 T:I.
Outb'd equivalent chord i08._, IN. 1.79,.,, 7+"I.
Ratio movablesurface chord/total surface chord .......
At Inb'd equiv, chord ......
At Outb'd equiv, chord ........
SweepBack Angles. degrees ............
LeadingEdge + h.%OO_ _":',[_. 1_5.OO _'_C.1
Hingeline +
Area Moment(Norm.I to h,nge line) .......
1977013202-025
/
_AZT;"7If (¢oncl_-'ea)
MODELCOMPONENT:'_.['G .; o.,
GENERALDESCRIPTION:_Tl_'. '-'O"_,,'iC,'T(_ATICI'T?T_,,_,,,L.._._,VLTOoOOOOn_(DTIV_:L .- I
) '_I_D %4TI_ T,O"',:"':;,';A":.P,_T'._,_T.9 t,TTIZ/v5.33P.,_T_.,C_,:,_T7r,_t_,T'rL.T.'__'O-Ill mllll,
' V, ' ,X'p !.---,-T,-_TI_O ._pT,_T,,r:r.:"P.;iTI,,%e,,{TO Tkr_,FU,gEIAG,_,._2ETI.FF_,T,I'7:). ,
,_*' ; ',T4 ¢,e,_#
DRAWINGNUMBER: :ZL_O-OOOOg3
DIMENSIONS: FULL-SCALE MO.D.ELSCALE .- --
TOTAL DATA
AreaPlanform _._90.0oo0sq._. io%1_,_._ T.,Wetted ......
Span (equivalent) _IN. _.AspectRatio P.c:5 r.,_ _Rateof Taper . l.!7"r,' i.]:"Taper Ratio ._hb .,_ooDihedralAng]e,degrees 3.!o_.DF,G. ,.,_.%0 r.','O.IncidenceAngle,degrees _.ooo....DFX}. _..¢c:,,_!_.r..AerodynamicTwist,degrees 3.o00 D_X_. _.C_ _':G.Toe-lnAngle ,li II m l
CantAng]e ....SweepBackAngles,degrees
LeadingEdge _5.oc0 nEo. ;_.oro _':_,.TrailingEdge -I0.,_0 Itt. ,-IO._':0_0.0.25 ElementLine 35.,_o_D_O. 3F,_.,,n,,::c..
Chords:
Root (WingSta.0.0) -_,_.pI_,II_. _i. T;:.Tip, (equivalent) I}',._,_ YI;. _.,,. ,,.MAC _7;_.]I IN. 7.ri 1 '.Fus.Sta.of .25MAC ll,_'.?,C._ I, IR. 1_"";" _":"W._. of .25 MAC _'_ ""- _,_, •-'i IlL _.C,l ,_""B.L. of .25MAC
AirfoiI SectionRootTip
EXPOSEDDAtA
Area !7_P.:29003_.,_T.., ,.,.:_ Z.',.IN.Span. (equivalent) T_o.,-,R ._. !I, ' _ '.Aspect Ratio P.O_ _.r",, "ll
TaperRatio _ ._,:_ii i •
ChordsRoot __Kp._O _1%1. ..,.9,__' l,;.
Tip I_i.q$ I_I. .'..r." .._;:.MAC __.,J_ -N. " '_:.': I,;.Fus. Sta. of .25 MAC ._i,'s.]i _z:;. i_. _,_ z'.W.P.of .25MAC ._on."O I':. ).'_'"n;.B.L. of .25 MAC l'i_3."_ _. _.':- _ T".
22
1977013202-026
!
JI
1977013202-027
1977013202-028
1977013202-029
,,,,4
O'3W
0
._P__.,.,0
1977013202-030
ORIGINAE PAGE IS
OF POoR QUALITI_ 27
1977013202-031
IW
Q
t#
!
28
1977013202-032
DATA FIGURES
29
1977013202-033
1977013202-034
1977013202-035
1977013202-036
1977013202-037
,?
I l _k,, :
-_
..J
' ' 5 ! -_ .......
k- ..... ; _ _ _ ..... .- ,
i
_ _i..___ _,_' .', / -
,__ ....,- - . ,- '-.......... -_
_I,_._ _ .... -..... ...,._...... ._,::: ,. : ..
--,- , , J __t_ I ........
j__ ! I I
1977013202-038
1977013202-039
i
I
1977013202-040
1977013202-041
" ! ! 1 1 1 _ Ii , t
: ' i I ! 1 t_, I ! ("_ I i l
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1977013202-123
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1977013202-127
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1977013202-129
1977013202-130
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1977013202-131
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1977013202-132
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1977013202-133
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1977013202-134
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1977013202-136
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1977013202-139
1977013202-140
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1977013202-141
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1977013202-142
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1977013202-143
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1977013202-144
1977013202-145
1977013202-146
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1977013202-147
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1977013202-148
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1977013202-149
1977013202-150
1977013202-151
1977013202-152
1977013202-153
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1977013202-154
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1977013202-156
1977013202-157
1977013202-158
APPFNDIX
TABUlaTED SOURCE DATA
Plotted data tabulations are av:_ab_e from DMS
on request.
1977013202-159
_ • • • : ....... ;-. • b ...... q ._ .£ . •|l|l|Jllllllll Illllllf|lll f
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1977013202-160
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_ +°°°°°°°°° .... +oo0o+o ......+' .+++ ++
+ . + _ _ ,_
+ +m++m++ooooooo +++ooo+ooo+++
1977013202-161
..... ___.._,_ _ .............
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...... _ . _ ": . . "1 _ .... _ -__ _ _ _ _ . .
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1977013202-162
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1977013202-163
°o,Q _°'°°°'' .... oo _o,oo° ..... ..o
.o ..... oo°oo .... o_*.°,°*o*
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g____ _ .............IIIIIIIIIII1| ltll|llll III
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