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)

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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

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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

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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