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The flow over a yawed circular cone is discussed with particular emphasis on the separation of boundary layer which occurs for sufficiently high incidences along a generator on the leeward side of the cone. Wind-tunnel experiments have been carried out for several Reynolds numbers, with a 9° half angle cone at M y = 7. For the test conditions, the boundary layer is transitional on the leeward side of the cone. The laminar region of the boundary layer is investigated theoretically by using a finite difference method which permits the effect of angle of attack on the behavior of the flow to be analyzed. The measured heat transfer rates, the direction of the limiting streamlines and separation generator (when / > / sep ) have been compared with theoretical results. A possible configuration of the flow near the wall, in the separated region, is discussed. NomenclatureC p = specific heat C = pu/p e n e i = angle of attack I = static enthalpy / = static enthalpy M' = (\/U e )(dWJd6} external flow parameter M -Mach number Pr = Prandtl number q = heat transfer rate Re = local Reynolds number per unit length, cm ~1 Re^ = freestream Reynolds number per unit length, cm" 1 Re x = local Reynolds number based on x abscissa T = I/I e , static enthalpy ratio 17, K, W= velocity components along the x, y, and directions u, u, w = transformed components of velocity x = coordinate along generators of cone y = coordinate normal to surface a = streamline direction y = ratio of specific heats 9 C . = semi vertex angle of cone 6 = (p sin 6 C azimuthal coordinate Y\ -similarity variable \ JL = absolute viscosity coefficient p = mass density = azimuth angle Subscripts e = external flow conditions cr = conditions corresponding to the critical incidence p ~ wall conditions sep = separation conditions 0 = stagnation conditions •DO = freestream conditions

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An extensive experimental study of the near wake of a 9° half-angle sharp cone at incidence at M∞, = 7 has been conducted. The model was suspended by six thin wires. The flow field in the plane of symmetry was surveyed from 0 to 2·5 diameters downstream of the base in the axial direction, and to the bow shock in the transverse direction. For three values of incidence (0° 5° and 15°))measurements were made of the static pressure, Pitot pressure and stagnation temperature, from which the streamline pattern was determined. In addition the u. = 0 line was found independently. The results of the measurements were also used to trace lines of constant Pitot pressure showing the shock waves, and lines of constant stagnation temperature in the viscous wake.