Experimental Study of Supersonic Flow Around Truncated Cones at Incidence

Results of an experimental study of supersonic flow around truncated cones with cone half-angles of 20, 30, and 40°, performed at Mach numbers M = 2, 3, and 4 within the range of angles of attack up to 20°, are presented. A relationship is established between the emergence of an internal shock wave and the character of pressure distribution along the generatrix of the truncated cone. It is shown that the known boundaries of regimes obtained for axisymmetric flow around sharp and blunt cones can be used to predict flow regimes in the vertical plane of symmetry of the truncated cone at incidence.