论文信息 - 6 Development of Micro Air Vehicles with in-Flight Adaptive Wing

6 Development of Micro Air Vehicles with in-Flight Adaptive Wing

A = aspect ratio (b2/S) b = wing span CD = drag coefficient = D/(0.5ρV 2S) CL = lift coefficient = L/(0.5ρV 2S) CL max = maximum lift coefficient CLα = lift-curve slope, 1/deg CM = pitching-moment coefficient about quarter-chord point of the root chord, = M/(0.5ρV 2S c) c0 = root chord measured along the longitudinal axis of the wing c = mean aerodynamic chord measured along the longitudinal axis D = drag force d = position of the maximum reflex hi = height of the maximum inverse camber hz = camber height at z cross section in spanwise direction h0 = camber height at the root of the wing L = lift force M = pitching moment about quarter-chord point of the root chord m = mass Re = mean-aerodynamic-chord Reynolds number S = wing planform area TP = thrust force

Sergey V Shkarayev | Motoyuki Aki | S. Shkarayev | M. Aki

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