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DR2Aerodynamic PDR IIAerodynamic Preliminary Design Review II
“The 20 Hour Marathon”
October 19, 2000
Presented By: Loren Garrison
Team DR2Chris CurtisChris PetersJeff Rodrian
Mark Blanton
DR2Aerodynamics PDR II• Presentation Outline
• Updated Aircraft Geometry
• Comparison of 3-D Lift and Drag Coefficients
• 3-D Lift, Drag, and Moment Coefficients with elevator deflection effects
• Maximum Endurance Flight Conditions
• Cmarc Developments
DR2Aerodynamics PDR II
• Wing Geometry- Airfoil: S 1210
- Taper Ratio: 1.0
- Dihedral Angle: 0 (deg)
- Sweep Angle: 0 (deg)
- Aspect Ratio: 8
- Span: 7.71 (ft)
- Root Chord: 0.96 (ft)
- Tip Chord: 0.96 (ft)
- Planform Area: 14.9 (ft2)
- Wetted Area: 29.7 (ft2)
DR2Aerodynamics PDR II
• Horizontal Tail Geometry- Airfoil: NACA 0006
- Taper Ratio: 0.75
- Dihedral Angle: 0 (deg)
- Sweep Angle: 4.0 (deg)
- Aspect Ratio: 4
- Span: 2.88 (ft)
- Root Chord: 0.82 (ft)
- Tip Chord: 0.62 (ft)
- Planform Area: 2.07 (ft2)
- Wetted Area: 4.22 (ft2)
DR2Aerodynamics PDR II
• Vertical Tail Geometry- Airfoil: NACA 0006
- Taper Ratio: 0.6
- Dihedral Angle: 0 (deg)
- Sweep Angle: 5.60 (deg)
- Aspect Ratio: 2.5
- Span: 1.81 (ft)
- Root Chord: 0.91 (ft)
- Tip Chord: 0.54 (ft)
- Planform Area: 1.31 (ft2)
- Wetted Area: 2.68 (ft2)
DR2Aerodynamic PDR II
DR2Aerodynamics PDR II
• 3-D Lift Curve (Roskam Method)
19.1
4/ )(cos44.4
1
chA
LwfL
htLLL
LLoL
KKKd
d
CKC
d
d
S
SCCC
CCC
wwf
hwf
DR2Aerodynamics PDR II
• 3-D Lift Curve (Roskam Method)
)3/1(
7.1A
2
1
3107
1
)1(
11
bl
bh
K
K
ARARK
h
h
h
DR2Aerodynamics PDR II
• 3-D Lift Curve (Roskam Method)
wLzllwLo
l
lwL
CiiC
eARC
CC
))(5.0(
3.571
DR2Aerodynamics PDR II
• 3-D Lift Curve Slope (Warner Method)
wLzllwLo
l
L
LLoL
CiiC
ARn
C
C
CCC
))(5.0(
21
1
*
,where n=1+for bu=bl
DR2Aerodynamics PDR II• 3-D Lift Curve (Warner Method)
and are determined from a curve fit to the data in Warner, Aircraft Design: Performance
9984.02979.5759.23595.62112.63
208.0226.00072.0
234
2
b
G
b
G
b
G
b
G
c
G
c
G
DR2Aerodynamics PDR II
• 3-D Drag Polar
2
2
LDoD
LDoD
CAR
nCC
eAR
CCC
(Roskam)
(Warner)
DR2Aerodynamics PDR II• 3-D Lift Curve for the Aircraft using the Roskam and Warner Methods
DR2Aerodynamics PDR II• 3-D Drag Polar for the Aircraft using the Roskam and Warner Methods
DR2Aerodynamics PDR II• 3-D L/D for the Aircraft using the Roskam and Warner Methods
DR2Aerodynamics PDR II• 3-D Endurance Parameter for the Aircraft using the Roskam and Warner Methods
DR2Aerodynamics PDR II• 3-D Lift Curve with Elevator Deflections
eCCCC eLLLoL **
• 3-D Lift Curve Slope (Warner Method)
21
1
ARn
Cl
CL ,where n=1+
DR2Aerodynamics PDR II• 3-D Lift Curve Slope (Warner Method)
9984.02979.5759.23595.62112.63
208.0226.00072.0
234
2
b
G
b
G
b
G
b
G
c
G
c
G
and are determined from a curve fit to the data in Warner, Aircraft Design: Performance
DR2Aerodynamics PDR II• 3-D Lift Curve with Elevator Deflections
ew
hthLhL
LLh
S
SCC
eE
eE
eE
CC
e
e
)1(221cos
1
DR2Aerodynamics PDR II• 3-D Moment Coefficient with Elevator Deflections
eCCCCemmmom
**
25.0725.0
31
180
20
1
1
)(
hnp
wLoo
Lhw
hthLw
Lhw
ht
w
acwLw
np
ohLhLohww
hthLo
w
npmh
ww
hthtmwmo
lx
c
ARC
dd
CSS
C
dd
CSS
cxC
x
iCCSc
SlC
c
xC
Sc
ScCC
DR2Aerodynamics PDR II• 3-D Moment Coefficient with Elevator Deflections
w
cgachL
w
hth
w
acwcgwLm
npwcg
Lhww
hthmh
ww
hthtm
eeehL
mh
c
xx
d
dC
S
S
c
xxCC
xcsmx
CSc
SlC
cS
cSC
EEEC
C
eee
e
1)(
*
)1()1(
DR2Aerodynamics PDR II
• 3-D Drag Polar with Elevator Deflections
2LDoD C
AR
nCC
DR2Aerodynamics PDR II• 3-D Coefficient Summary
CLo = 0.5095
CL= 3.4566 rad-1
CLe = 0.3218 rad-1
Cmo = 0.5907
Cm = -0.5623 rad-1
Cme = -1.2253 rad-1
CDo = 0.0175
DR2Aerodynamics PDR II• 3-D Lift Curve with Elevator Deflections
DR2Aerodynamics PDR II• 3-D Moment Coefficient with Elevator Deflections
DR2Aerodynamics PDR II• 3-D Drag Polar with Elevator Deflections
DR2Aerodynamics PDR II• 3-D L/D with Elevator Deflections
DR2Aerodynamics PDR II• 3-D Maximum L/D
DR2Aerodynamics PDR II• 3-D Endurance Parameter
DR2Aerodynamics PDR II
• Flight Conditions for Maximum Endurance
Vloiter = 23.9 ft/s
Angle of Attack = 6.61 deg
CL = 0.91
CD = 0.0701
• Maximum L/D
L/Dmax = 15.0
DR2Aerodynamics PDR II
DR2Aerodynamics PDR II• Future Tasks
• Extract CL and CD values from the Cmarc model to compare to the theory
• Run the Cmarc stability test to determine the aerodynamic derivatives and
compare to the theory
• Evaluate the Trim ability, Stability, and Controllability considerations