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Vehicle Sizing PDR. AAE 451 Fall 2006 Team Whishy Washy Tung TranMark Koch Matt Drodofsky Matt Lossmann Ravi PatelKi-bom Kim Haris Md IshakAndrew Martin. Historical Data. Cessna 182. Alpha 40 Trainer. High King Tech. Nitro Airstrike. Historical Data. - PowerPoint PPT Presentation
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Vehicle Sizing PDR
AAE 451Fall 2006
Team Whishy Washy
Tung Tran Mark KochMatt Drodofsky Matt Lossmann
Ravi Patel Ki-bom KimHaris Md Ishak Andrew Martin
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Historical Data
Aircraft Model Weight (lbs)
without Payload
Super Cub RTF Electric 1.6245
Cessna 182 1.1325
Alpha 40 Trainer 5.25
Megatech Nitro Airstrike Rc Airplane 5.5
Hign King Tech. model # CTF0026 2.425
Alpha 40 TrainerCessna 182
Nitro AirstrikeHigh King Tech
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Historical Data
• The historical was used to get a approximate estimate of the weight for our models.– The data chosen based on their physical similarities
to our concept– The range is significant because it shows our concept
can easily be adjusted for sizing references
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Weight Estimate
• Raymer Method– Find the weight fractions for different flight phases
• Warm-up - .002• Take off - .02• Climbing - .0002334• Loiter level flight - .0083• Loiter turning flight - .0117• Landing – approximately the same as takeoff
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Weight Estimate
• Combine each phase to determine the battery weight fraction– Validated results with the weight_3.m Matlab file
– Wtot = Wp + We + Wb
– Plot W – We vs. W
– Plot the Historical data vs. W– The historical data trend line is .2103*W+.1243– The battery used was the Lithium Polymer
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Weight Estimation
• Battery– Lithium Polymer
• Volts per cell – 3.7 V• Milliamp hours per cell – 1500 mA• Grams per cell – 36 g• The energy density is 2.517E+05 Joules per lb
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0 1 2 3 4 5 6 7 8 9 100
1
2
3
4
5
6
7
8
9
10
Weight~lbf
W-W
e an
d W
b+W
p~lb
f
Estimated aircraft weight is 5.2103 pounds.
Weight estimation using historical weight data
Estimated battery weight is 0.22002 pounds. Payload weight is 1 pound.
Historical data
Estimated weightHistorical data (Foam airplane w/o payload)
Weight Estimation
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Weight Estimation
• The intersection is the estimated weight of the aircraft– W = 5.2013 lbs– The battery weight is .22 lbs
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Constraints
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Constraints• Values Used in Constrain Diagram
– L/D = 10– Climb (gamma) = 35deg
– Vclimb = 80ft/sec
– CLmax = 1.4
– Vstall = 30 ft/sec
– Vcr = 130 ft/sec
– CDO = .022
– Φ = 45 deg
– Sland = 120 ft
– μ = .05
– ηp = .6
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CLmax Constraint
• Historical Data– AAE 451 Aerodynamics Sourcebook
• Thin Airfoil Based– NACA 4412 Example
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Historical Database
• Max CL values from Aerodynamics Sourcebook
CLmax(no flaps) CLmax (flaps)
Gulfstream I ~1.2 ~1.4
SIAI-Marchetti S-211
~1.2 ~1.5
Cessna 310 ~1 ~1.2
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Thin Airfoil Theory
0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4
•NACA 4412
–Naca4geo.m
–Sourvort.m
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Thin Airfoil Theory
• 2-D Cla– Cla derived from curve
fitting Cl-alpha plot
• 3-D CLa
• Total CLaCLCLeARClCl
CL
1
flapsa CLCLCL
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Thin Aifoil Theory
..
2
..2 cos
lh
f
Da
lhf
Daa
aflaps
S
S
S
S
CLCL
•Added CL due to flaps
Ratio of flapped area to total wing area
Sweep angle of flap hinge
2-D change in alpha max
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Thin Airfoil Theory
• ResultsCla ~7.6
CLa ~5.3
CLflap ~.22
CLmax ~1.2-1.4
•Good Agreement with Historical Data
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Constraints
• Turn Constraint Equation– Q = rho at S.L
– V = Vcr
– CDo = .022
– A = 7– E = .8– ηp = .6
– N =1/cos(45)
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Constraints
• Land distance constraint– Sland = 120 ft
– CLmax = 1.4
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Constraint
• Take off– μ = .05
– CDO = .022
– ηp = .6
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Constraints
• Cruise– Vcr = 130 ft/sec
– CDO = .022
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Constraints
• Stall– Vstall = 30 ft/sec
– CLmax = 1.4
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Constraints
• Climb Constraint– ηp = .6
– Vclimb = 80ft/sec
– Climb (gamma) = 35deg– L/D = 10
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Aircraft Size
• Weight – 5.2103 lbs
• Horse power – 1.3
• Wing area – 3.47 ft2