NEAR WAKE OF A SLENDER CONE AT LARGE ANGLE OF ATTACK
POLYTECHNIC INST OF BROOKLYN FARMINGDALE NY DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS
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The near wake of a sharp, slender cone at an angle of attack equal to the half-cone angle 10 deg is studied experimentally. Tests were run at two different Reynolds numbers these correspond to 1 completely laminar flow on the surface Re 150,000 and, 2 laminar flow on the windward and turbulent on the leeward surface Re 550,000. The nature of the surface boundary layer was determined by measuring the surface heat transfer over a wide range of test Reynolds numbers 60,000 or Re or 1,200,000 and comparing the data with theoretical analyses. Wake data obtained correspond to radial profiles taken in the plane of symmetry total temperature, pitot, and static pressures are measured from the rear stagnation point to approximately seven diameters downstream of the base. Centerline distributions of Mach number, stagnation pressure, and static temperature are computed and compared to the corresponding results at zero angle of attack.
- Guided Missiles
- Fluid Mechanics