Cylindrically blunted wedges were tested in a hotshot tunnel at various angles of attack at a Maeh number of about twenty. The geometry was so arranged that the sonic point occurred either on the nose or much further downstream on the corner terminating the body, depending on angle of attack. Both surface pressures and shock shapes were obtained over the range in incidence associated with this large change in sonic point body thickness. The rearward shift of the sonic point was found to have very little effect on the flow for a relatively slender blunted wedge. The role of asymmetry in the stagnation region was explored by comparing a nonslender blunted wedge at small incidence to the slender wedge at large incidence. Coordinates are discussed which allow representation of both shock shapes and surface pressures of small afterbody flow deflection theory together with blast wave theory. In these coordinates, pressure and shock from the present large flow deflection experiments on the slender wedge (up to loss of asymptotic wedge flow) also correlate, independent of the position of the sonic point.