The Wright Brothers: First Aeronautical Engineers and Test Pilots

Abstract

CD = drag coef cient CL = lift coef cient CLt = lift coef cient (tail) CLw = lift coef cient (wing) Cm = pitchingmoment coef cient Cm ac = pitchingmoment coef cient (aircraft) Cm cg = pitchingmoment coef cient about the center of gravity c = wing chord D = drag force Fx = x component of force Fy = y component of force g = accelerationdue to gravity H = NVt dCLt=dCL h = fraction of chord K = gain in control law, proportional control L = lift force `np = separation of center of gravity and neutral point `t0 = distance between aerodynamic centers of canard and wing M = mass m = pitchingmoment mnp = pitchingmoment about neutral point p = rate of rotation qt = dynamic pressure at a horizontal lifting surface q1 = dynamic pressure, 12V 2 1 r = yaw rate S = wing area T = thrust force Tµ1 = low-frequency factor Tµ2 = high-frequencyfactorNu = average forward translationalvelocityNVt = dimensionless tail volume, ´t `t0St=cS V1 = ight speed