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