Analysis and design of wing-body combinations at subsonic and supersonic speeds.

The method of aerodynamic influence coefficients has proved to be an effective tool for the analysis and design of wings, bodies, and wing-body combinations at supersonic speeds. This paper describes the extension of this method into the subsonic flow regime, and correlates the theory with experiment over a wide speed range. The method may be applied to the calculation of the pressures and forces acting on arbitrary wing-body combinations in steady flight, including aeroelastic effects, and to the design of wing camber surfaces in the presence of a body. Nomenclature A = aspect ratio b = span c =. chord C = aerodynamic coefficient d = distance / = singularity distribution function F = distribution function K = constant I = body length L — panel sweep M = Mach number r = radius Re = real part u, v, w = perturbation velocities U = freestream velocity x, y, z = Cartesian coordinates a. = angle of attack 0 = angular coordinate, panel inclination X = taper ratio A = leading edge sweep £, rj = integration variables <p = velocity potential Subscripts D = drag k = corner point L = lift M — moment n — number p = pressure r = radial a. = per radian 0 = tangential oo = freestream condition