Abstract:
Part I is an introduction to an empirical and theoretical study of two-dimensional aerofoil flows which include a limited region of supersonic flow terminated by a shock wave. A brief review of theoretical studies of the problem is followed by a detailed analysis of the flow pattern and associated pressure distribution. A scheme for the analysis of measured pressure distributions is thus derived, and this is used in Part II of the present paper to construct a semi-empirical method for the estimation of pressure distributions. The implications of the results established by this analysis are discussed in relation to the development of transonic aerofoil flows. In Part III the results of an integral solution of the transonic flow equation are examined, and modified on the basis of the analysis of Part II.
