team 1 aerodyn1qdr

7/27/2019 Team 1 Aerodyn1qdr

1/18

Dane Batema Benoit Blier

Drew Capps Patricia Roman

Kyle Ryan Audrey Serra

John Tapee Carlos Vergara

Team 1:

Aerodynamics 1 QDR

Team Canard

September 19th, 2006


2/18

AAE 451 Team 1 2

Overview

Aircraft Geometry:

- Airfoil selection for wing and tail

- Wing and tail configuration

- Aspect ratio and wetted area

- 3-View drawing

Aerodynamic Mathematical Model:

- CL

- CD

- CLMax

Summary


3/18

AAE 451 Team 1 3

Preliminary Airfoil Selection

Wing Airfoil:- Looked at pylon racers

- MH 43 common airfoil

- Low Reynolds number airfoil

Tail Airfoil:

- NACA 0009 common in tail surfaces

- Thin, lower induced and parasite drag

MH 43

NACA 0009


4/18

AAE 451 Team 1 4

Wing Geometry

METHOD Fixed thanks to historical data:

Aspect ratio = 10

Taper ratio = 0.45

To be determined:

Sweep angle

Dihedral angle

Wing span


5/18

AAE 451 Team 1 5

Wing Geometry

C

ab

s

Swing= 4.16 ft2

22

bac

Swing

45.0a

b

10

4 2

wingS

c

f ta 89.0

f tb 4.0

f tc 225.3

Wing span = 6.45 ft

Wing span = 6 ft Aspect ratio = 8.65

Sweep angle = )(tan 1

c

ba

= 9.3 degrees

Too much for structure

Top View


6/18

AAE 451 Team 1 6

Wing Geometry

dtroot

ttip

Dihedral angle= )(tan 1

c

tt tiproot =0.73 degrees

Chordtip= 0.4 Chordroot

ttip= 0.4 trootSame airfoil all along the wing

0846.0c

t

troot= 0.0846 Chordroot troot= 0.0753 ft

ttip= 0.0338 ft

From the airfoil section, we know :

Front View

ttip= 0.0846 Chordtip


7/18

AAE 451 Team 1 7

Tail Geometry

Vertical tail :

Horizontal tail :

Taper ratio : 0.6

Aspect ratio : 10

Sweep angle : 11.4 deg

No dihedral 1.88 ft

0.47 ft0.28 ft

11.4 deg

Shtail= 0.36 ft2

Top View

D

AACSS

wing

htail

3.0

0.7 ft

0.65 ft

Degrees of freedom on the size for control and stability

withSwing = 4.16 ft

2

AAC = 0.65 ft

D = 2.25 ft


8/18

AAE 451 Team 1 8

Wing and Tail Geometry

Wing Horizontal Tail

Span 6 ft 1.88 ft

Sweep

Angle 9.3 11.4

Taper Ratio 0.45 0.6

Dihedral

Angle 0.73 0


9/18

AAE 451 Team 1 9

Aircraft Wetted Area

5.1aircraft

span

L

W

ftWspan 6

(Historical data)ftLaircraft 4

ftHaircraft 45.0

ftWaircraft 27.0

2

3210 579.0 ftAAAAA tttttop 2

321 117.1 ftAAAA sssside


10/18

AAE 451 Team 1 10

Aircraft Wetted Area

)2

(4.3 sidetop

wet

AAS

Fuselage wetted area estimate :

Wing/tail wetted area estimate :osedwet SS exp021.2

Horizontal tail : Sexposed-htail = 0.33 ft2

Vertical tail : Sexposed-vtail = 0.196 ft2

Wing : Sexposed-wing = 3.92 ft2

Fuselage : Swet-fuselage = 2.88 ft2

vtailwethtailwetwingwetfuselagewetaircraftwet SSSSS

286.11 ftS aircraftwet

Swet-wing = 7.92 ft2

Swet-htail = 0.67 ft2

Swet-vtail = 0.39 ft2


11/18

AAE 451 Team 1 11

3-View Drawing


12/18

AAE 451 Team 1 12

Mathematical Model

CL:-

CD:-

CLMax:- CLat stall

2

LoDD kCCC

2

AR

ARCC lL


13/18

AAE 451 Team 1 13

Mathematical Model

2D Estimation from XFOIL

2D Coefficients

Clo= 0.151

Cl= 0.104/

Clmax= 1.082

Cl vs Alpha

-0.6

-0.4

-0.2

0

0.2

0.4

0.6

0.8

1

1.2

-10 -5 0 5 10 15

Alpha (deg)

Cl


14/18

AAE 451 Team 1 14

Mathematical Model

2D Estimation Cont

2D Drag Coefficients

Cdo= 0.00589

Drag Polar

0

0.02

0.04

0.06

0.08

0.1

0.12

0.14

0.16

-0.5 0 0.5 1 1.5

Cl

Cd


15/18

AAE 451 Team 1 15

2D to 3D Calculations

Find e :64.0)045.01(78.1 68.0 Ae

793.0e

Aek

1

Find k :

0464.0k

Find CDo:

ref

wetfDoSSCC

0157.0DoC

Find CLfrom lifting line :

2

AR

ARCC lL

845.0max LC

Find CDfor 3D :

2

LDoD kCCC


16/18

AAE 451 Team 1 16

2D/3D Comparison

2D plotted in blue3D plotted in red

Lift Coefficient

-0.6

-0.4

-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

-10 -5 0 5 10 15

Alpha (deg)

Cl

Drag Polar

0

0.02

0.04

0.06

0.08

0.1

0.12

0.14

0.16

-1 -0.5 0 0.5 1 1.5

Cl

Cd


17/18

AAE 451 Team 1 17

Summery

Aircraft Geometry:- Airfoil selection for wing and tail

- Wing and tail configuration

- Aspect ratio and wetted area

- 3-View drawing

Aerodynamic Mathematical Model:

- CL

- CD

- CLMax


18/18

AAE 451 Team 1 18

Questions

Any Questions?

team 1 aerodyn1qdr

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