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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 1–1 Aircraft Performance • Accelerated horizontal ﬂight- 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 ﬂight dt and L − W = Define L = • 1 2 ρV 2 SC L where – ρ – 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 ρV 2 dynamic pressure – V = speed relative to the air Fall 2004 16.333 1–2 – C L lift coeﬃcient – for low Mach number, C L = C L α ( α − α ) 3 α angle of incidence of wind to the wing 3 α is the angle associated with zero lift • Back to the performance: 1 L = ρV 2 SC L and L = mg 2 2 mg which implies that V = ρSC L so that V ∝ C − 1 / 2 L and we can relate the effect of speed to wing lift...
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## This note was uploaded on 11/07/2011 for the course AERO 16.333 taught by Professor Alexandremegretski during the Fall '04 term at MIT.

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

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