The flow about a body of revolution at high supersonic airspeeds is investigated analytically with the aid of the generalized shock-expansion method. With the assumption that flow at the vertex is conical, approxi¬mate solutions for the flow field are obtained for values of the hyper¬sonic similarity parameter (i.e., the ratio of the free-stream Mach number to the fineness ratio of the body) greater than about 1 and for angles of attack less than the semivertex angle of the body. Surface streamlines are approximated by meridian lines and the flow field is calculated in meridian planes. Simple explicit expressions are obtained for the surface Mach numbers and pressures in the special case of slender bodies.nIn the case of lifting cones, algebraic solutions defining the entire flow field are obtained when the hypersonic similarity parameter has a value of about 1.4 or greater.nSurface pressures and shock-wave shapes were obtained experimentally at Mach numbers from 3.00 to 5.05 and angles of attack up to 15° for two ogives having fineness ratios of 3 and 5 and for two cones having the same vertex angles as the ogives. The predictions of the methods of this paper are found to be in good agreement with experiment at values of the hypersonic similarity parameter in the neighborhood of 1 and greater, when the ratio of angle of attack to semivertex angle is about one-half, or less. For increasing values of this ratio, agreement deteriorates but may still be considered fair for values slightly less than 1.
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