This report treats the kernel function of the integral equation that relates a known or prescribed downwash distribution to an unknown lift distribution for harmonically oscillating wings in supersonic flow. The treatment is essentially an extension to supersonic flow of the treatment green in NACA Report 1234 for subsonic flow. For the supersonic case the kernel function is derived by use of a suitable form of acoustic doubled intention which employs a cutoff or Heariside unit function. The kernel functions are reduced to forms that can be accurately evaluated by considering the functions in two parts: a part in which the singularities are isolated and analytically expressed, and a nonsingular part which can be tabulated.
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