A physical theory of supersonic aerofoils in unsteady flow

Abstract

Solutions for point and line sources are given, for the `transient ’ case only, in both stationary and moving co-ordinate systems. These are then integrated to give the solutions for a supersonic aerofoil ( a ) entering a sharp-edged gust, ( b )following a sudden change of incidence. The method of obtaining oscillatory (flutter) solutions from ( b ) comes next, and it is Finally, the results of some calculations on the entry of supersonic aircraft into gusts are given. These results are in non-dimensional form and cover a fairly wide range of speeds, wing loadings and gust profiles. shown that these solutions check with those of Temple & Jahn (1945) and hence with others The failure of Collar’s simplified theory (Collar 1944) is also explained.