The effect of the boundary layer upon the flow in a conical hypersonic wind tunnel nozzle

Integral equations for the flow in a conical hypersonic nozzle with a thick boundary layer have been formulated and some approximate solutions of these equations have been studied. A method developed by Burke for calculating boundary layer thickness using empirical correlations has been extended to a relatively broad range of stagnation conditions and has been used to compute the effect of boundary layer development upon hypersonic nozzle flow. (Author)