Oscillatory Supersonic Kernel Function Method for Isolated Wings

The method presented uses a collocation technique with the supersonic kernel function to solve lifting surface problems on isolated wings in steady or oscillatory flow. A set of pressure functions are developed based on conical flow theory solutions which account for discontinuities in the supersonic pressure distributions. These functions permit faster solution convergence than is possible with conventional supersonic pressure functions. The method is compared with other theories and experiment for a variety of cases. Nomenclature a = freestream speed of sound, m/sec a = conical coordinate AR = aspect ratio |8 = supersonic Prandtl-Glauert factor, /32 = M2 - 1 &REF = reference length, meters — usually % wing chord for twodimensional flow or % MAC for finite wings in threedimensional flow 6(77) = wing semichord at span station ??, nondimensionalized by &REF Cp =

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