aae 451 aircraft design aerodynamic preliminary design review #2 team members oneeb bhutta, matthew...
TRANSCRIPT
![Page 1: AAE 451 Aircraft Design Aerodynamic Preliminary Design Review #2 Team Members Oneeb Bhutta, Matthew Basiletti, Ryan Beech, Mike Van Meter](https://reader034.vdocuments.net/reader034/viewer/2022051401/56649ccb5503460f94994def/html5/thumbnails/1.jpg)
AAE 451 Aircraft Design
Aerodynamic Preliminary Design Review #2
Team Members
Oneeb Bhutta, Matthew Basiletti , Ryan Beech, Mike Van Meter
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Presentation Overview
Aircraft Geometry
Aerodynamic Modeling
Stability and Control Derivatives
Testing Status and To-Be-Finished
Concerns
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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
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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
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Parasite Drag For Fuselage, booms & pods
d
lf
400100
601
3
f
fFF
fFF
35.01
(Ref. Raymer eq.12.31 & eq.12.33)
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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)
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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
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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
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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)
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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
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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
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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
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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.
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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
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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!