TWO-DIMENSIONAL ROTATIONAL FLOW AT HIGH MACH NUMBER PAST THIN AEROFOILS

Abstract

In this paper a theory of flow at high Mach number past thin aerofoils is developed and a critical survey of previous papers given. The essential feature of the paper is the establishment of a general similitude, given first by Hayes, which expresses the fact that the problem of determining the two-dimensional flow at high Mach number past a thin aerofoil is in the limit analytically identical with that of unsteady onedimonsional flow produced by the motion of a piston. The error involved here is shown to be a factor of the form , where M₀ is the undisturbed stream Mach number. Using this similitude a note on the effect of entropy is given.