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MAE 4291: Senior Design 1Oral Update
Steve Bukowsky Chris BuonocoreAnthony CostantiniJoshua Gauvin Omar Hayan Michael HanlonMarco Herrera
Ben HolohanSyrus JeanesKarl LindmanStephan Mehling Rob RadomskiTed Simeoni Kurt Walford
Project Overview Project Goal Project Objectives Junior Design Accomplishments
Summer Contributions
Next Phase of Project Fall and Spring
The goal of the project is to demonstrate the potential uses of a channel wing aircraft. Channel wing craft possess the potential to take over many, simple roles that would otherwise be filled by expensive and maintenance-intensive rotary-winged craft. It is our intent to prove that channel wings are a viable alternative to helicopters for many roles. Compared to Straight Wing Drag, Lift, and Stall Characteristics Potential Military and Commercial Surveillance Applications
www.airandground.com Robert J. Englar “Experimental Development and Evaluation of Pneumatic Powered-Lift Super-STOL Aircraft”
www.airandground.com
Channel Wing Lift Validation Design Prototype Aircraft Design and Construct Prototype Wing For Testing Purposes Design and Construct Complete Working Prototype Perform Flight Tests Using Prototype Model Refine Prototype Through Wind Tunnel Tests and Construct
Dedicated VTOL Aircraft Add Payload for Distinct Missions
Robert J. Englar Robert J. Englar
Channel Wing VTOL Prototype
Design, Develop, and Test Channel Wing Prove Channel Wing Lift Concept Record Flight Characteristics of Channel Wing Record Wind Tunnel Data for Channel Wing Perform Analysis of Data Design, Develop, Test, and Fly Prototype Develop VTOL Channel Wing Prototype Compare to Conventional Straight Wings
Initial Concept Studies and Preliminary Design Literature Review Preliminary CAD Drawings Initial Calculations Design Showcase Poster Board and Concept Handout Prelim Manufacturing: Fuselages, Wings, and Structural Tests Prelim Wind Tunnel Testing
P reliminary Analys is
mphSC
WV
LTO 07.53
22.1
max
2375.02 ftDcS 17.82
S
bAR
07.02
0, eAR
CCC LDD
lbDL
WT 189.0
85.15D
L
C
C
D
L
WAC
CWP
L
D 152
3
23
P reliminary Analys is
Vertic al T ake-off Ang leα=tan-1(T 0/L 0)
1953 wind tunnel tes t of C C W-5 us ing NAC A 4418
α=tan-1(800/340)=67°
Vertical take-off angle for C C W-5 is 67°
α
T0
L
0
T 0cos (α)=L 0s in(α)
L VT O L = T 0s in(α)+L 0cos (α)
Prototype Development
Concept Handout
Fuselage Testing
Application of Systems Engineering Engine to Channel Wing Project
Design ArchitectureRequirements and ActionsTeam structureProject Life-Cycle Phases Project Management and SE Engine Cost effectiveness Risk Assessment
RC Flying Time by Team members Channel Wing Lift Stand Design Wind Tunnel Test Design Channel Wing Website Refined Channel Wing Lift Research
NASA Systems Engineering HandbookRev. Dec 2007
Technical Documents
Fall Conduct Wind Tunnel Testing
9 in. Straight9 in. Channel14.15 in. Straight
Construct Test Aircraft for Piloting Experience Based On Wind Tunnel Results, Make New Channel Design (If
Necessary) Tailored For VTOL Make VTOL Capable Craft and Fly Use Flight Characteristics/Wind Tunnel Data and Compare to
Theory
Spring Continue Flight Testing Continue Comparative Theoretical Analysis