Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 1 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

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 2 Historical Data Aircraft ModelWeight (lbs) without Payload Super Cub RTF Electric Cessna Alpha 40 Trainer5.25 Megatech Nitro Airstrike Rc Airplane 5.5 Hign King Tech. model # CTF Alpha 40 Trainer Cessna 182 Nitro Airstrike High King Tech

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 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

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 4 Weight Estimate Raymer Method –Find the weight fractions for different flight phases Warm-up Take off -.02 Climbing Loiter level flight Loiter turning flight Landing – approximately the same as takeoff

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 5 Weight Estimate Combine each phase to determine the battery weight fraction –Validated results with the weight_3.m Matlab file –W tot = W p + W e + W b –Plot W – W e vs. W –Plot the Historical data vs. W –The historical data trend line is.2103*W –The battery used was the Lithium Polymer

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 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

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 7 Weight Estimation

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 8 Weight Estimation The intersection is the estimated weight of the aircraft –W = lbs –The battery weight is.22 lbs

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 9 Constraints

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 10 Constraints Values Used in Constrain Diagram –L/D = 10 –Climb (gamma) = 35deg –V climb = 80ft/sec –CL max = 1.4 –V stall = 30 ft/sec –V cr = 130 ft/sec –C DO =.022 –Φ = 45 deg –S land = 120 ft –μ =.05 –η p =.6

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 11 CL max Constraint Historical Data –AAE 451 Aerodynamics Sourcebook Thin Airfoil Based –NACA 4412 Example

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 12 Historical Database Max CL values from Aerodynamics Sourcebook CL max (no flaps)CL max (flaps) Gulfstream I~1.2~1.4 SIAI-Marchetti S-211 ~1.2~1.5 Cessna 310~1~1.2

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 13 Thin Airfoil Theory NACA 4412 –Naca4geo.m –Sourvort.m

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 14 Thin Airfoil Theory 2-D Cla –Cla derived from curve fitting Cl-alpha plot 3-D CLa Total CL

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 15 Thin Aifoil Theory Added CL due to flaps Ratio of flapped area to total wing area Sweep angle of flap hinge 2-D change in alpha max

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 16 Thin Airfoil Theory Results Cla~7.6 CLa~5.3 CL flap ~.22 CL max ~ Good Agreement with Historical Data

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 17 Constraints Turn Constraint Equation –Q = rho at S.L –V = V cr –C Do =.022 –A = 7 –E =.8 –η p =.6 –N =1/cos(45)

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 18 Constraints Land distance constraint –S land = 120 ft –CL max = 1.4

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 19 Constraint Take off –μ =.05 –C DO =.022 –η p =.6

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 20 Constraints Cruise –V cr = 130 ft/sec –C DO =.022

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 21 Constraints Stall –V stall = 30 ft/sec –CL max = 1.4

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 22 Constraints Climb Constraint –η p =.6 –V climb = 80ft/sec –Climb (gamma) = 35deg –L/D = 10

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 23 Aircraft Size Weight – lbs Horse power – 1.3 Wing area – 3.47 ft 2