MEM425F11_HW7 - : 0.25 Coefficient of moment about the...

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Home work #7 (due 11/08/11) Problem 1 : A jet-engine aircraft with the characteristics given below has been designed so that its level cruise flight (i.e., max_range flight) can be maintained with zero elevator deflection. Determine the elevator deflection required to maintain a level loiter (i.e., max_endurance) flight . Characteristics : Zero-lift moment coefficient about c.g., = 0.05 Lift-curve slope, a = 0.09 deg -1 Parasite drag coefficient, = 0.02 Drag polar parameter, K = 0.05 Tail volume ratio, V H = 0.3 Elevator effectiveness, = 0.04 deg -1 Problem 2 : A few wind tunnel experiments conducted on a wing-body shape (with a wing area S of 250 m 2 , and a chord c of 2 m ), have resulted in the following data: Lift curve slope, a : 0.075 deg -1 Aerodynamic center location,
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Unformatted text preview: : 0.25 Coefficient of moment about the aero-center :-0.03 Zero-lift downwash angle, : 0 deg Downwash angle slope, : 0.25 deg-1 A horizontal stabilizer/tail (with no elevator) with a plan area S t of 2.5 m 2 and a lift curve slope a t of 0.1 /deg , is given to you. For a c.g. location, h = 0.2 determine the horizontal location of the tail and the tail setting angle , to ensure a static margin SM of 0.15 , and that the a/c can be trimmed at an angle of attack of 5 deg . (assume that the tail is relatively of negligible mass) Problem 3 : Assume that the aircraft in Problem 2 weighs 10,000N (with h = 0.2; SM = 0.15 ). How far behind the cg can a passenger of mass 60kg ( 588.4 N ) be seated to ensure a statically stable airplane?...
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This note was uploaded on 01/10/2012 for the course MEM 425 taught by Professor Yousuff during the Fall '08 term at Drexel.

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