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lecture_1 - 16.333: Lecture #1 Equilibrium States Aircraft...

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Unformatted text preview: 16.333: Lecture #1 Equilibrium States Aircraft performance Introduction to basic terms Fall 2004 16.333 11 Aircraft Performance Accelerated horizontal ight- balance of forces Engine thrust T Lift L ( to V ) Drag D ( to V ) Weight W dV D T mg L T D = m = for steady ight dt and L W = Define L = 1 2 V 2 SC L where air density (standard tables) S gross wing area = c b , c = mean chord b = wing span AR wing aspect ratio = b/c c t c 0 kc k edge b = 2.s c Sweepback angle Trailing Q = 1 2 V 2 dynamic pressure V = speed relative to the air Fall 2004 16.333 12 C L lift coecient for low Mach number, C L = C L ( ) 3 angle of incidence of wind to the wing 3 is the angle associated with zero lift Back to the performance: 1 L = V 2 SC L and L = mg 2 2 mg which implies that V = SC L so that V C 1 / 2 L and we can relate the effect of speed to wing lift...
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lecture_1 - 16.333: Lecture #1 Equilibrium States Aircraft...

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