Measurements of the turbulent near wake of a cone at Mach 6.

Abstract

Abstract : A detailed investigation of the flow properties in the turbulent near wake of a circular cone and an elliptic cone was conducted. Both the circular cone and the elliptic cone were at zero angle of attack in a Mach 6 flow. The experiments were conducted at a stagnation pressure of 800 psia with a corresponding free stream Reynolds number of 14.4 million per foot. The boundary layer at the cone shoulder was turbulent for the entire test series. Detailed radial profiles of the total temperature, total and static pressures in the supersonic regions of the wake at several axial stations are presented. In addition, the static and total pressure along the centerline of symmetry in the recirculation zone, the u=o line, and the properties at the cone shoulder prior to the expansion into the base are also presented. Correlations of the distance to the downstream stagnation point, the maximum static pressure rise at the wake neck, and the axial static pressure along the axis of symmetry are made with other experimental data. (Author)