MIT16_842F09_assn4

MIT16_842F09_assn4 - Vehicle Design and Performance You may...

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Vehicle Design and Performance You may answer no more tharl of the foilowillg two questions: A. Vehicle Design and Performance (Aeronautics) B. Vehicle Design and Performance (Astronautics)
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Vehicle Design and Performance (Aeronautics) An aircraft sizing study is performed, using -the following independent design parameters. m gross takeoff mass C takeoff wing loading Aa aspect ratio f airfoil thicknessJchord ratio CL lift coefficient From these, simple structural, aera, powcrplant, and weight models are then used to derive numerous relevant dependent parameters. Sorn~ examples are b = \lrnsAR/z wing span v 21 0. 5b3 /A2 wing (fuel) volume V=Jw flightspeedattakeoffmass fk = VSJvb average-chord Reynolds number HFC = PSK(mengi,, , . . .) power-specific fuel consuxnption CD = C2 JTAI + cdp(&, CLv i) + . . . drag coefficient Mruei = m(l- f,,) - mstructure(m, C, A?. . .) - mengine . . . allowable fuel mass A payload/gross mass fraction of f,, = O,l is assumed, The assumed structural material properties correspond to common composites. The Breguet range is then finally examined, ultimately as a function of the independent parameters. In a sizing study, the gross mass is varied over a wide range rn = I . . .I00 000 kg (small UAV large transport). All the other irldepcndent parameters are optimized so as to maximize range R
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MIT16_842F09_assn4 - Vehicle Design and Performance You may...

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