This report contains an analysis of the surface-pressure distributions on two aerofoil sections of 10% thickness/chord ratio, at Mach numbers near 2 and 4, and at Reynolds numbers between 93 and 1920, based on model chord. It is shown that with the exception of those hole positions within the upstream influence of the trailing-edge, all surface pressures over a wide range of incidence may be correlated using a viscous-interaction parameter x in a manner similar to that for the flat plate at zero incidence. For the front surfaces of the double-wedge aerofoil, the local inviscid flow conditions near these surfaces represent those of the equivalent free stream where these are used in formulating the appropriate value of X. For the rear wedge surfaces, and for the biconvex surfaces, correlation is achieved if it is assumed that the equivalent local flow only attains some fraction (about 0.6) of the surface expansion from the shoulder or the leading edge respectively.
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