aae 451 aircraft design first flight boiler xpress november 21, 2000 team members oneeb bhutta,...
TRANSCRIPT
![Page 1: AAE 451 Aircraft Design First Flight Boiler Xpress November 21, 2000 Team Members Oneeb Bhutta, Matthew Basiletti, Ryan Beech, Mike Van Meter Professor](https://reader036.vdocument.in/reader036/viewer/2022062323/5697bf7c1a28abf838c84095/html5/thumbnails/1.jpg)
AAE 451 Aircraft Design
First FlightBoiler Xpress
November 21, 2000
Team MembersOneeb Bhutta, Matthew Basiletti , Ryan Beech, Mike Van
Meter
Professor Dominick Andrisani
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11ft
6ft
3-D Views
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Aerodynamic Design Issues
Lift
• Low Reynolds Number Regime
• Slow Flight Requirements
Drag
• Power Requirements
• Accurate Performance Predications
Stability and Control
• Trimmability
• Roll Rate Derivatives
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Low Reynolds Number Challenges
•Laminar Flow -more Prone to Separation
•Airfoil Sections designed for Full-sized Aircraft don’t work well for below Rn=800,000
•Our Aircraft Rn=100,000-250,000
Separation Bubble-to be avoided!
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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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Drag Prediction Assume Parabolic Drag Polar
2
0 LDD KCCC +=
AeK
π1
= 75.0=e Based on Empirical Fit of Existing Aircraft
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Parasite Drag
ref
wetfDo S
QFFSCC =
(Ref. Raymer eq.12.27 & eq.12.30)
=
58.2(Re)10log
455.02.1fC
Drag Build-up Method of Raymer
Blasius’ Turbulent Flat Plate- Adjusted for Assumed Surface Roughness
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Drag Polar
0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.80
0.02
0.04
0.06
0.08
0.1
0.12
0.14
0.16
Aircraft Drag Polar
CL
CD CDiCDo
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Power Required
15 20 25 30 35 4016
18
20
22
24
26
28
30
32
Velocity [ft/s]
Po
wer
Req
uir
ed [
ft-l
b/s
]
Predict:• Power required for cruise
• Battery energy for cruise
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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 = 1.53CLcruise = 1.05Xcg = 0.10-0.38 (% MAC)Static Margin = 0.12 at Xcg = 0.35
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Stability Diagram
elev deflect=-8 deg
-4
0
4
8
0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8-0.4
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
CL
Cm
cg
elev deflect=-8 deg
-4
0
4
8
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Flow Simulation
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Parasite Drag CDo for Wing and Tail surfaces
( ) [ ]18.04
34.11006.01 Mct
cx
ct
FFWing
++=
d
lf =
+++=
400100
601
3
f
fFFFuselagef
FFPOD
35.01+=
(Ref. Raymer eq.12.31 & eq.12.33)
For Fuselage, booms & pods
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Tail GeometryHorizontal Tail:Area = 2.2Span = 3.0ft Chord = 0.73ftVh = 0.50
Sc
Sxv hh
h =
Vertical Tail- 25% added
Area = 1.75 sq.ftSpan = 1.63 ft Chord = 0.60 ftVv = 0. 044
Sb
SXV vv
v =
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Control Surface Sizing:Elevator
Area Ratio = 0.30 Chord = 2.7 in.
Rudder Area Ratio = 0.40
Single rudder of chord = 7.5 in.
AileronsArea Ratio = 0.10Aileron chord = 3 in.
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Equipment Layout & CG.
Rotation angle = 10deg
Tip Back angle= 15deg
Controls equipmentPropulsion componentAirframe component
17.54 in.
Miscellaneous Weight
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Equipment Layout (3-D)
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Landing Loads
Vland=1.3Vstall=25ft/s
lbinVKe vertgW −== 6.72
21
kkSdsWorkd
5.00
==For d = 1 in., k = 15.2 lb/in
= -5 degVvert=2.2ft/s
For 1 inch strut travel, peak load = 15.2 lb
spar = 240 psi on landing
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Static Margin, Aerodynamic Center, and c.g.
Xac = 0.46
Xcg = 0.35
SM = 0.11
cgac XXSM −=
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Horizontal and Vertical Tail Sizing
v
refvv x
bSVS =
h
refhh x
cSVS =
Vh - Horizontal tail volume coefficient = 0.50Vv - Vertical tail volume coefficient = 0.044
22.2 ftSh = 275.1 ftSv =
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Control Surface Sizing Based on historical data from
Roskam Part II Tables 8.1 and 8.2.
ref
a
S
S
v
r
S
S
h
e
S
S
Homebuilts Single Engine
0.095 0.08
0.42 0.36
0.44 0.42
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Control Surface Sizing (cont.) Sa = 1.35ft2
Sr = 0.80ft2
Se = 1.00ft2
Max. surface deflection is 15 deg.
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Climb Performance Max. Climb Angle, G
√↵
−
=Γ −
W
DT1sin
G = 7.3 deg.
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Turning Performance Maximum turn rater = 50ft
Vmax = 28ft/s
Y= 0.28 rad/s
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Propulsion Design Issues
PowerPower requiredPower available
EnduranceCan we complete the mission
VerificationMotor test to take place this week
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Power
Power required is determined by aircraftPower available comes from the motor 15 20 25 30 35 40 45 50
15
20
25
30
35
40
45
50
55
Velocity [ft/s]
Power Required [ft-lb/s]
Power Required Power Available
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System EfficienciesPropeller
60-65%
Gearbox95%
Motor90%
Speed Controller95%
Total System Efficiency
50.7%
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System Components
PropellerFreudenthaler 16x15 and 14x8 folding
Gearbox“MonsterBox” (6:1,7:1,9.6:1)
MotorTurbo 10 GT (10 cells)
Speed ControllerMX-50
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Economics
Preliminary Design525 man-hours @ $75 = $39,375
Testing50 man-hours @ $75 = $3,750$81.70 in materials
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Economics
Prototype Manufacturing300 man-hours @ $75 = $22,500$417.35 in materials
Flight Testing$900
Prototype manufacturing budget$200 max
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The Budget
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Total Project Cost The Bottom Line
$67,024.05
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Questions?