Abstract:
Summary. The equations of motion for supersonic flow over a symmetrical wing at zero incidence are linearised and the pressure coefficient at a point in the wing mean plane is expressed in terms of the finite part of a singular integral. The equation is modified in such a way that the finite part can be calculated analytically, leaving a regular integral to be evaluated numerically. A method of correcting this value of pressure coefficient, to enable an estimate of the value on the wing surface to be made, is discussed. Numerical results for three wings are given and compared with previous results and with experiment.
