An accurate and effective method for calculations of unsteady three-dimensional supersonic flow has been developed. The present method is capable of handling general cases of planar, coplanar, and nonplanar wing planforms in the complete frequency domain. A harmonic-gradient potential model is provided for elementary doublet panels to be made compatible with the wave number generated. Consequently the number of panel elements required is least affected by the given Mach number and reduced frequency. Thus, the required panel number can be optimized to as few as 30, a fraction of the number required by the existing methods. To assess the accuracy and effectiveness of the present method, comparison with various available data is given. AC P h i L m M (x,y,z) (X,Y,Z) a. CO Subscripts J T.E. Nomenclature = lifting pressure coefficient = structural mode shapes = reference chord length = slope of leading or trailing edge of the panel element = freestream Mach number = wing-fixed coordinates; (x,y,z) = (X/$L, Y/L, Z/L) (see Fig. 1) = control point location in (x,y,z) coordinates = true physical coordinates = position of leading or trailing edge of the panel element at 77 = 0 = moving coordinates (see Fig. 1) = oscillatory potential = modified velocity potential = ^e ikMX = doublet solution of modified potential = circular frequency of harmonic motion = index of the number of chordwise element in the yth strip = index of the number of strip -trailing edge of the wing -wake

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