An air afterglow flow visualization apparatus and free molecule probe were used to determine shock detachment distances for blunt bodies in the range 1.8 < M < 2.8 and 100 < Re/inch < 1200. Cylindrical models were used to develop the experimental techniques and reasonable agreement was shown between detachment distances measured by afterglow and free molecule probe techniques. Spherical model detachment distances were obtained by the afterglow technique and when corrected for boundary layer effects showed satisfactory agreement with the predictions of Heybey, provided isentropic flow existed between the shock wave and the boundary layer. It was concluded that shock detachment distances in rarefied gas flows depend on Reynolds as well as Mach number.
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