ESDU 82005 presents results, for use in flutter calculations, obtained from a computer program. The program embodies a method for evaluating the forces, moments and pressure distributions on a thin aerofoil oscillating harmonically with small amplitude in supersonic flow. The calculations were made for three modes of oscillation: aerofoil heave and pitch, and motion of a trailing-edge control surface with its hinge-line at 0.8 of the aerofoil chord. The results are presented in the form of tabulated airforce coefficients over a frequency parameter range from 0 to 2.0 and a Mach number range from 1.02 to 5.0. In addition, illustrative graphs are presented to show the effect of frequency and Mach number on oscillatory load distribution in heave and pitch.