AAE 451 Aircraft Design

Aerodynamic Preliminary Design Review #2

Team Members

Oneeb Bhutta, Matthew Basiletti , Ryan Beech, Mike Van Meter

Presentation Overview

Aircraft Geometry

Aerodynamic Modeling

Stability and Control Derivatives

Testing Status and To-Be-Finished

Concerns

Geometry and Configuration

Wing:•Sref = 13.5 sq.ft.•Span = 11 ft.•Aspect Ratio = 9•Taper Ratio = 0.6 tip section•Airfoil: S1220

Horizontal Stabilizer:•Area = 2.2 sq ft.•Span = 3.0 ft.

Vertical Stabilizer:•Total Area: 1.75 sq.ft.

11.1’Boiler Xpress

Airfoil Selection

Wing:Selig S1210

CLmax = 1.53 Incidence= 3 deg

Tail sections:flat plate for Low ReIncidence = -5 deg

Re = 150e3

0

0.01

0.02

0.03

0.04

0.05

0.06

-0.2 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8 2 2.2

Cl

Cd

FX63-137

S1210

S1223

Parasite Drag For Fuselage, booms & pods

d

lf

400100

601

3

f

fFF

fFF

35.01

(Ref. Raymer eq.12.31 & eq.12.33)

Parasite Drag

58.2(Re)10log

455.0fC

CDo for Wing and Tail surfaces

18.04

34.11006.01 Mct

cxct

FF

ref

wetfDo S

QFFSCC

(Ref. Raymer eq.12.27 & eq.12.30)

Tail GeometryHorizontal Tail:Area = 2.2Span = 3.0ft Chord = 0.73ftVh = 0.50

Sc

Sxv hhh

Vertical Tail- 25% added

Area = 1.75 sq.ftSpan = 1.63 ft Chord = 0.60 ftVv = 0. 044

Sb

SXV vvv

Drag Polar

0 0.5 1 1.5 2 2.50

0.05

0.1

0.15

0.2

0.25

0.3

0.35Airfoil Selig 1210

CL

CD CDiCDo

CD

Drag vs Velocity

15 20 25 30 35 400

0.2

0.4

0.6

0.8

1

1.2

1.4Airfoil Selig 1210

Velocity ft/s

Total Drag Induced Drag

Drag (lb)

Aerodynamic Properties

Wetted area = 44.5 sq.ft.Span Efficiency Factor = 0.75CL=5.3 / rad

CL e = 0.4749 /radL/Dmax = 15.5Vloiter = 24 ft/sCLmax = 1.55CLcruise = 1.05Xcg = 0.10-0.38 (% MAC)Static Margin = 0.12 at Xcg = 0.35

Stability Diagrams

-8 -6 -4 -2 0 2 4 6 8-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

alpha (deg)

Cm

cg

elev deflect= -8 deg-4 0 4 8

Stability Diagrams

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

CL

Cm

cg

elev deflect=-8 deg-4 0 4 8

Control Surface Sizing:Elevator

Area Ratio = 0.45 Chord = 4 in.

Rudder Area Ratio = 0.40

Single rudder of chord = 7.5 in.

AileronsArea Ratio = 0.10Aileron chord = 3 in.

Testing Status and TBF:

Model wing nearly complete

Wind tunnel test with wake survey next week

CMARC model of wing to predict derivatives

Calculate Dihedral angle required

Use wake data to predict propeller flowfield

Concerns Will we get the CLmax we are aiming for? Are the stability derivatives for ailerons correct? Will there be a variable stability system

for it to matter? Will I be around for it to matter? Can we get some covering material to stick

to the foam without looking like someone’s kid brother made it?

Are the drag and power requirements correct to prevent being underpowered?

STAY TUNED!