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Vehicle Sizing PDR

Vehicle Sizing PDR. AAE 451 Fall 2006 Team Whishy Washy Tung Tran Mark Koch Matt Drodofsky Matt Lossmann Ravi Patel Ki-bom Kim Haris Md Ishak Andrew Martin. Historical Data. Cessna 182. Alpha 40 Trainer. High King Tech. Nitro Airstrike. Historical Data .

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Vehicle Sizing PDR

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  1. Vehicle Sizing PDR AAE 451 Fall 2006 Team Whishy Washy Tung Tran Mark Koch Matt Drodofsky Matt Lossmann Ravi Patel Ki-bom Kim Haris Md Ishak Andrew Martin

  2. Historical Data Cessna 182 Alpha 40 Trainer High King Tech Nitro Airstrike

  3. 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

  4. 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

  5. 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

  6. 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

  7. Weight Estimation

  8. Weight Estimation • The intersection is the estimated weight of the aircraft • W = 5.2013 lbs • The battery weight is .22 lbs

  9. Constraints

  10. 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

  11. CLmax Constraint • Historical Data • AAE 451 Aerodynamics Sourcebook • Thin Airfoil Based • NACA 4412 Example

  12. Historical Database • Max CL values from Aerodynamics Sourcebook

  13. Thin Airfoil Theory • NACA 4412 • Naca4geo.m • Sourvort.m

  14. 2-D Cla Cla derived from curve fitting Cl-alpha plot 3-D CLa Total CL Thin Airfoil Theory

  15. Thin Aifoil Theory • Added CL due to flaps 2-D change in alpha max Ratio of flapped area to total wing area Sweep angle of flap hinge

  16. Thin Airfoil Theory • Results • Good Agreement with Historical Data

  17. Constraints • Turn Constraint Equation • Q = rho at S.L • V = Vcr • CDo = .022 • A = 7 • E = .8 • ηp = .6 • N =1/cos(45)

  18. Constraints • Land distance constraint • Sland = 120 ft • CLmax = 1.4

  19. Constraint • Take off • μ = .05 • CDO = .022 • ηp = .6

  20. Constraints • Cruise • Vcr = 130 ft/sec • CDO = .022

  21. Constraints • Stall • Vstall = 30 ft/sec • CLmax = 1.4

  22. Constraints • Climb Constraint • ηp = .6 • Vclimb = 80ft/sec • Climb (gamma) = 35deg • L/D = 10

  23. Aircraft Size • Weight – 5.2103 lbs • Horse power – 1.3 • Wing area – 3.47 ft2

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