aeromorph presentation (initial)
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ADAPTIVE LEADINGEDGE DROOP MECHANIS
CHRIS, REIDY
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PRIVATE AIRCRAFT
STALLING
ANGLEFIXEDWINGCUFF
ADAPTIVEWING CUFF
DESIGNPROCESS
2D DESIGN
3D DESIGN
INTERNALMECHANISM
MATERIALS
STALLING ANGLE
FUELCONSUMPTIONMONETARY
SAVINGSCARBONFOOTPRINT
P R O B
L E M
S O L U
T I O N
A D V A
N T A G E S
1 2 3 4
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PRIVATE AIRCRAFT
STALLING
ANGLEFIXEDWINGCUFF
P R O B
L E M
1
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At high angles of attack, privateaircraft undergo stalling caused byseparation of airflow.
Stalling causes sudden drop in lift,resulting in loss of pilot control.
Fixed leading edge droop malleviates airflow separationincreases stalling angle.
However, it increases drag angles of attack.
STALLING ANGLE PRIVATE AIRCRAFT
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ADAPTIVEWING CUFF
DESIGNPROCESS
2D DESIGN
3D DESIGN
INTERNALMECHANISM
MATERIALS
S O L U
T I O N
2
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RESEARCHFINALDESIG
N
MODELIN
ACCOMPLISHING THE FINAL DESIGN DESIGN PROCESS
THE IDEAFUEL
EFFICIENCYFLIGHT SAFETY
PRIVATE AIRCRAFTSPECIFICATIONS
FIXED LEADINGEDGE CUFFS
AIRFOIL AND WINGDESIGN AND ANALYSIS C
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FLIGHT ADAPTABILITY DROOP MECHANISM
The mechanism can modify angle of leading edge droop during flight. Alleviates stalling conditions Increases fuel efficiency
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CESSNA SKYCATCHER FLIGHT CONDITIONS
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FLIGHT CONDITION OPTIMAL DRAG AIRFOIL OPTIMAL STALLING AIRFOIL L/D
Climb #1 15 Cuff 15 Cuff 125.5
Climb #2 15 Cuff 20 Cuff 133.5
Cruise #1 15 Cuff 20 Cuff 133.0
Cruise #2 15 Cuff 20 Cuff 135.6
Descent #1 15 Cuff 20 Cuff 130.1
Descent #2 15 Cuff 20 Cuff 119.8
OPTIMAL AIRFOILS FOR CRUISE & STALLINGAIRFOIL SELECTION
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BASELINE MODELCESSNA SKYCATCHER
WING CUFF MODEL
3D GEOMETRY WING DESIGN
AUTODESK
INVENTOR
FUSION
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AIRFLOW CONTOURS WING CFD ANALYSIS
WITHOUTCUFF
WITH CUFF
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PARTICLE IMAGE VELOCIMETRYWIND TUNNEL ANALYSIS
CRUISE CONDITIONS STALLINGCONDITIONS
BASELINE
12.5 CUFF
20 CUFF
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MOTILE APPARATUS FOR DROOP MODIFICATIONINTERNAL MECHANISM DES
Force = 160 lb
Weight = 10.7 lb Factor of Safety = 2.5
LINEAR ACTUATOR
FINAL INTERNAL MECHANISMIS LINEAR ACTUATOR
BECAUSE IT HAS HIGHERFACTOR OF SAFETY FORAPPROXIMATELY SAME
WEIGHT.
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STALLING ANGLE
FUELCONSUMPTIONMONETARYSAVINGS
CARBONFOOTPRINT
A D V A
N T A G E S
3
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MONETARY SAVINGS AND CARBON FOOTPRINTGREEN TECHNOLOGY
COMPARED TOBASELINE
520 Th gal fuel $3.227 M 9.575 M lb CO 2 200 Th trees
COMPARED TOFIXED CUFF
630 Th gal fuel $3.902 M 11.577 M lb CO 2 240 Th trees
THE ADAPTIVE LEADING EDGE DROOPIS MORE FUEL EFFICIENT
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INCREASED STALLING ANGLEFLIGHT SAFETY
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4
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MAKINGOUR DESIGN A REALITYNEXT STEP PLAN
Step4
Step3
Step2
Step1
Obtain insurance andpatent for design
Propose design andbudget to major
funding organizations
Obtain requiredresources and
facilities to constructdesign
Perform flight tfinal aircraft
perform inspe
PROTECTION FUNDING DEVELOPMENT VERIFICATIO
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IDENTIFYING POTENTIAL INVESTORSTARGET MARKET
PRIVATE
PILOTS
Pre-Market
ManufacturingCessna, GKN Aerospace,
etc.
Private Aircraft Companies
Aviation and Aerospace Industry
1. Pitching the design to private aircrmanufacturers such as Cessna
2. Licensed to private manufacturersproduction
Governmenbe pursued, Departmenand of Ene
the Fe Ad
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INVESTMENT SOURCES FUNDING MECHANISMS
G
PRIVATE INVESTMENT
1. Major source of funding will be private aircraftcompanies who invest in our design in order toimplement it in their own aircraft and accrueincreased sales / profits in the future.
2. In recent years, government has been pushing forsafer and more fuel efficient transportation, whichis the goal of our project. Government grants will
be pursued from Departments of Energy andTransportation, and Federal Aviation Administration.
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COMPETITIVE REFERENCE
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ATTRIBUTE FIXED WING CUFFS VARIABLE SLATS STOL KITS
Flight Safety
Fuel Efficiency
Price
Ease of Usage
ASSESSMENT
PRODUCT ASSESSMENT COMPETITIVE REFERENCE
ENDORSEMENT
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INCREASING STALLING ANGLEENDORSEMENT
Professionals in the aeronauticalalready shown interest in our dethis endorsement from Pratt &Dr. Manoj Rahematpura .
We are also currently working toGKN Aerospace .
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