WIND TUNNEL INVESTIGATION OF THE TURBULENT NEAR WAKE OF A CONE AT ANGLE OF ATTACK
GENERAL APPLIED SCIENCE LABS INC WESTBURY NY WESTBURY United States
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Aerodynamic measurements were made in the turbulent near wake of 10 deg. half angle circular cone at a 10 deg. angle of attack. The experiments were conducted at Mach 6 with a stagnation pressure of 800 psi and a corresponding free stream unit Reynolds number of 14.4 million per foot. The Reynolds number was sufficiently large so that the boundary layer at the cone shoulder was turbulent. Detailed radial profiles of the total and static pressures along the meridian plane of symmetry in the supersonic regions of the wake at several axial stations are presented. In addition, the shape of the u 0 line in the meridian plane of symmetry was also obtained. Correlations are shown for nearwake data obtained for zero angle of attack.