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7/24/2019 Sailplane Wing Optimization
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Foot Launch SailplaneWing Optimization
Presented by:
Constantin Nicolinco
Ahmad Kalai
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!ntroductionSailplanes: aircra"ts #ithout engines
Launched $ia aero to#% #inch%slingshot% or e$en automobile to#
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!ntroduction&ost Sailplanes optimized "or crosscountry soaring
Narro# and slender #ings% lo# drag%but high ta'e(o) speed
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&aupin Carbon *ragon*e$eloped in the late +,-s
*esigned "or "oot launch
.(LOF o"//01 m2s
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Problem StatementMinimize the takeof speed o the
Carbon Dragon microlit sailplane by
changing several wing parameters,while maintaining the wing loadingunder !kg"m# and a total empty
weight o no more than $%kg&
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Wor' *istributionConstantin N
Structure Optimizer
45isting *esign 6e$ie# 6eport Writing
Ahmad K
Aerodynamic Sol$er
&*F !ntegration CA*
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45isting Con7gurationParameter Value
Length 10/ m
Wingspan /809/ m
Wing Area /9091 m;
Aspect Ratio /01:/Airfoil Cul$er S*
Root Chord 1/0 in
Tip Chord 0< in
G Limits =2( >0
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*esign .ariables%
Constraints% andParameters%esign Varia#les
Wing span
@aper ratio
6oot chord
Parameter
Cruise Altitude
Air"oil
&aterial
Fuselage and 4mpennage
Weight and Structure
Constraint Value "S&$&a5 @a'eo) Speed D /, m2s
&@OW D >, 'gWingspan D /< m
&a5 Wing Load D /+ 'g2m&a5 Wing
*eEection
D , degrees
&inimum 6oot
Air"oil @hic'ness
,0,< m
@aper 6atio , D G /
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&*O Architecture andOptimizer
&*F Architecture
H0A0 OptimizerH0A0 Optimizer
Structural Sol$erBFinite 4lement Iased
Aerodynamic Sol$erB&odi7ed @ornado
*esign.ariables
*esign.ariables Weight&a5 CL
Forces G&oments
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Aerodynamic Sol$er .L&
&odi7ed $ersion o"
@ornado 4liminates user input
Automates Analysis
Obtains CLma5
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CLma5 *etermination
Created a ne# "unction #ithin@ornado
!ncreases angle o" attac' untilany section goes abo$e limit
Limit obtained using the *
ma5 CL
Conser$ati$e approach sincestops #hene$er a singlesection stalls
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.alidation Cessna />
NACA 9/
Span: 8
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Structural Sol$erFinite 4lement based B/, elements
Sa"ety "actor o"
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