22 - transonic aerodynamics(1).pdf
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Number
Mitigatingthe
Drag
Problem
Thesupercriticalairfoil
Sweep
TheArea
Rule
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NACA0012AT8DEGREES
-10
M
-
-8
-7
M=0
0.1
0.2
0.3
-16
-14
-12
Cpmin2
1
1
M
CC
p
p
-
-5
-4
--Cp
.
0.5
0.6
0.7M
-10
-8
-6
-2
-1
.
0.9 -4
-2
0
1
0.0 0.2 0.4 0.6 0.8 1.0x/c
0 0.5 1M
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PRESSURECOEFFIENTWHERETHELOCALMACHNUMBERIS1
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PRESSURECOEFFIENTWHERETHELOCALMACHNUMBERIS1
)1(11
12
21
M
-16
)1(2
12
2
1
M
CR
-14
-12
CpCR
-10
-8
-
-4
-2
0
0 0.2 0.4 0.6 0.8 1M
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)1(11 12
21
M
2
minmin
1
1
M
CpCp
-16
)1(212
21 M
CR
M
-14
-12
-
-8
-
MCR
-4
-2
0
0 0.2 0.4 0.6 0.8 1M
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)1(11 12
21
M
2
minmin
1
1
M
CpCp
-16
)1(212
21 M
CR
-14
-120012at8de .-
-8
-
MCR MCR
-4
-2
.
0
0 0.2 0.4 0.6 0.8 1M
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M=0.5
INVISCIDCALCULATION
= .
.
Ilan Kroo and J Alonso Stanford Universit
http://adg.stanford.edu/aa241/drag/dragrise.html
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ShockInduced
Separation
www.hq.nasa.gov/pao/History/SP-
440/ch7-2.htm
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NACA2315
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NACA2315
M
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Sweep
T eAreaRu e
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DesignedtomaximizeMDIV
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NACA0012at2.3deg. oe ng at eg.
0.8
0.4
p L .L .
0.0
0.4
0 0.5 1 0 0.5 1
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htt : oea.larc.nasa. ov PAIS Conce t2R
eality/supercritical.html
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cosMM n
M
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cosMM n
M
R.T.Jones,HighSpeedWingTheory,
PrincetonUniversity
Press,
1960
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EffectsonLift
M
cosMM n
M
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2cos2
22
cos1 M
L
cosMM n
M
FigureA,4forg,P42
R.T.Jones,HighSpeedWingTheory,
PrincetonUniversity
Press,
1960
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2cos2
22
cos1 M
L
cosMM n
M
FigureA,4h,P43
R.T.
Jones,
HighSpeedWingTheory,
PrincetonUniversityPress,1960
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THESEARSHAACKBODY
2/32)/(18
)( LxV
xA
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TheAreaRule
Whitcomb,R.,1952AStudyoftheZeroLiftDragRise
CharacteristicsofWingBodyCombinationsNearthe
SpeedofSound,NACA
RM
L52H08
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747200B(AirForce1),MaxMach0.89
747
400,
Max
Mach
0.92
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Atsu ersonicMachnumberstheAreaismeasured
along
the
Mach
plane
instead
of
perpendicular
to
the
flightdirection
p ma s apes ormoregenera requ remen s efinitebaseareas,arearequirementsatparticularcross
sections)
aregiven
by
W.T.
Lord
and
E.
Eminton in
SlenderBodiesofMinimumWaveDrag,JournaloftheAeronauticalSciences,August,1954,pages569
. . ,http://www.aoe.vt.edu/~mason/Mason_f/MRsoft.html#MINDRAG