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?