-
7/28/2019 Wing Design 4
1/16
GroupName:TeamJDEMemberNames:DidumD.Abraham
ErikM.Petersen
Class:Aero.Engr.461
Date:Thursday,
May
07,
2009
-
7/28/2019 Wing Design 4
2/16
verv ew Desi nDirective
DesignProblem
Solution
Assumptions
Procedure
Design
Flow
Chart
(NSA)
Results
Solution ualit
PerturbationStudy
Conclusion
References
-
7/28/2019 Wing Design 4
3/16
DesignDirective
To
construct
a
main
wing
for
an
aircraft
Theaircraftconfigurationhasthefollowingcharacteristics:
,
CruiseAltitude=30,000ft
MaxEngine
Thrust
at
30,000
ft
=1000
lbf
CruiseT rott eSetting=80%
AircraftRange=1500miles
En ineTSFC at 0,000ft=1+ *M/8
M=Mach
Number
of
aircraft
Thedesignobjectiveistomaximizeaircraftcruisevelocity
-
7/28/2019 Wing Design 4
4/16
DesignProblemSolution
TheSystem
ControlVariables=8
Maximumcamber,locationofmaximumcamber,maximumthickness
Sweep,twist,
tapered,
root
chord,
and
span
Constraints=4
Wingliftcoefficientmustnotexceed1.2
ng
oa ngresu
mus
no
excee
30
ps
Totalweightfuelmustnotexceed60%oftheaircraftsweight
Achievableminimumrangeis1500miles
-
7/28/2019 Wing Design 4
5/16
Assumptions
Constantcruise
altitude
Noturbulenceorwindgusts
Nosloshing/centerofgravityproblems
Thewing
is
swept,
tapered,
and
twisted
ThewingiscomposedofairfoilsectionoftheNACA4DigitSeries
-
7/28/2019 Wing Design 4
6/16
ssump ons on nue Thewin characteristicsaredefinedb three
parameters: Maximumcambertochordratio
Locationofmaximumcambertochordratio
Maximumcamber
thickness
to
chord
ratio
Examp ewit NA A4412
4 =max.camberinhundredthsofchord
=
.
12=max.thicknessinhundredthsofchord
-
7/28/2019 Wing Design 4
7/16
Procedure
-
7/28/2019 Wing Design 4
8/16
ProcedureContinued
Method
used Newtoniterativescheme
p m za on rocess
SetupConmin()
Objfun()
Driver()
Global.h Startoptimizing
-
7/28/2019 Wing Design 4
9/16
t tu e 30000 tAirdensity 8.90617E004
slugs/ft^3Range 7916.7973mi
Pressure 629.43952
lbf/ft^2
Planformarea 350.135226843058
.
Angleofattack 7.53deg
spectratio 12.82
SpanEfficiencyFactor 1.0000
Volume 133.03 ft^3
Velocity 640.5996ft/s
Machnumber 0.644378
WingCL 0.90117
WingCdi 1.91257E002
CLConstraint 1.0708857
FuelConstraint 0.28325709 .
Rootangleofattack 7.5 12.3
SpanwiseStation,sp 21
WLConstraint 0.0030207
Ran eConstraint 6 16.
MCLpointsateachsp 11
Surfacepointsateachsp 20Iterations 10
-
7/28/2019 Wing Design 4
10/16
ResultsContinued
t=0.10,c=0.0011,pc=0.4,taper=0.42,twist=2.97deg,span= 0 t,c o r
= . 1 t,sweep=14. 9 eg
-
7/28/2019 Wing Design 4
11/16
ResultsContinued
-
7/28/2019 Wing Design 4
12/16
ResultsContinued
-
7/28/2019 Wing Design 4
13/16
SolutionQuality
Solution
seems
reasonable
and
reliable
Fewerstepsinnsa()reducerunningtime,butalso
solution
quality
Complexproblemswithmanycontrolvariablesrequire
-
7/28/2019 Wing Design 4
14/16
PerturbationStudyVariableName PerformanceIndex%
Altitude, alt 616.69646
e g t, 14.1729
Density(alt,p,T) 611.27398
-
7/28/2019 Wing Design 4
15/16
Conclusion
More
control
variables
add
more
complexity Longerruntimes;moreworktime
Many
plots
to
create
and
choose
from orecare u exam nat onm g t ea to etter
understandingofdesignspace
-
7/28/2019 Wing Design 4
16/16
References , . . .
ProfessorHindman.
20
April,
2009.
.
ToolBoxCompany.
The
Engineering
ToolBox.
Unit
onverter.2005. n s.20 pr ,2009.
.
