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ORION AEROSPACE. Aerodynamics Preliminary Design Review #2 October 23, 2000. Bridget Fitzpatrick Patrick Dempsey Heather Garber Keith Hout Jong Soo Mok. ORION AEROSPACE. Objectives. -Three View Drawing Update -Coefficient of Lift -Methods Update: Warner and Roskam -Drag Polar - PowerPoint PPT Presentation
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Objectives-Three View Drawing Update
-Coefficient of Lift
-Methods Update: Warner and Roskam
-Drag Polar
-Lift to Drag Curve
-Endurance Parameter
-CMARC Update
-Aerodynamic Effectiveness of the Control Surfaces
-Stability Derivatives
Aircraft Geometry – 3-View
SID5
Method
Clmax
Warner 1.25
Roskam
1.48
Average
1.37
2-D 1.53
Coefficient of Lift
Aerodynamic Mathematical Model WARNER
eCLCLoCLCL eol )(
CdstrutCdCdhtailCdvtailCdfuselageCdwingCDo lg
ARe
CLCDi
2
CDiCDoCD
)( ohhh iS
ShhCLCLowfCLo
2/
11
AR
n
ddCld
dCl
b
Aerodynamic mathematical model
Roskam
19.1
4/ )(cos44.4
1
chA
LwfL
htLLL
LLoL
KKKd
d
CKC
d
d
S
SCCC
CCC
wwf
hwf
3-D Coefficient of Lift
Aerodynamic mathematical model
Roskam
wfwlu LoLwwLo
h
h
h
CiiC
b
l
b
h
K
K
ARARK
))(5.0(
2
1
3107
1
)1(
11
)3/1(
7.1A
3-D Coefficient of Lift
Aerodynamic mathematical model
Roskam
eARC
CC
l
lL
3.571
3-D Coefficient of Lift Slope
Aerodynamic mathematical model
Roskam
3-D Coefficient of Drag
CDiCDoCD
18.1)(
2
)1(22
22
2
strutilverticaltatailhorizontalwingfuselage CdCdCdCdCdCdo
rr
re
ARe
CLCDi
3-D Drag Polar
Optimum CL~1
Lift to Drag Ratio
Endurance Parameter: CD
CL23
Endurance:
CLS
W
V
SCL
WV
SCLVWL
eqnVoplugandCLforsolve
numberkCLCDo
CL
kCLCDoCD
numberCD
CL
)(2
2
5.
...int.....
2
2
2
2
3
2
2
3
Flight Conditions for maximum endurance
L/D max:7.2
Velocity: 20.52ft/s
Angle of Attack: 8.37 degrees
CL: 1.03
CD: 0.16
Coefficient of Moment
Coefficient of Moment Calculations
)1(1
)1(
))((
/
d
dX
S
S
CL
CLd
dx
S
S
CL
CLx
x
iCLCLSc
SlCL
c
xCm
Sc
ScCmCm
achw
hh
w
h
achw
hh
w
hbodyacwing
ohhohww
hhw
wh
ww
hhwo
)1(
d
dCL
Sc
SlCm
cS
cSCm h
ww
hheh
ww
hhe
Equations taken from Mark Peters thesis
Coefficient of Moment Calculations
)1(
d
dCL
Sc
SlCL
c
xCm h
ww
hhw
w
eeCmCmCmoCm
Equations taken from Mark Peters thesis
Aircraft Geometry
SMxxcg -SM: the static margin was set at 0.18
Aircraft Geometry
Aircraft wetted Area
59.5 ft2
Wing 38.7 ft2
Struts 0.83 ft2
Tails 9.01 ft2
Landing gear -0.003 ft2
Aspect ratio of wing
4.4
Control Surfaces
Raymer’s Suggestions
Orion Aerospace
Ailerons 15-25% chord
15% chordfull span
Elevator 25-50% chord
40% chord full span
Rudder 25-50% chord
40% chord full span
Aerodynamic Effectiveness of the control surfaces
Rudder Effectiveness: 60%
Elevator Effectiveness: 60%
Aileron Effectiveness: 30%
Effectiveness determined from Roskam’s Flight Dynamics and Controls
Stability Derivatives
-Theoretical Method: This was presented on Tuesday.
-Will be compared to CMARC
CMARC needs:
-working wake
-will use to verify theoretical derivatives
Aerodynamic coefficients
e
CL 3.938
CLwing 3.7914
CLo .5242
Cm -.4428
Cmo .5503-.5992
Cm -.8667
CDo .0427
Questions?