SOME PRELIMINARY EXPERIMENTS ON PROBE INTERFERENCE IN HYPERSONIC NEAR WAKES
POLYTECHNIC INST OF BROOKLYN NY DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS
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Preliminary results concerning the effects of probing the recirculation region of a slender cone in hypersonic flow with conventional diagnostic techniques are presented. Experiments were performed at a free stream Mach number of 11.8 and unit Reynolds number of 600,000 per foot on a 5 degree half-angle cone with a base diameter of 10 in. The centerline axis of the recirculation region was investigated with various probes extended from the base probe diameters were roughly one-hundredth of the base diameter while base pressure at the base centerline and centerline pitot pressure at a station in the supersonic near wake were monitored. Similar studies were made while monitoring only the stagnation temperature profile in the supersonic near wake. It was found, for the above experimental conditions at least, that probes placed along the axis distorted downstream pitot pressures while off-axis curved probes did not appreciably alter either base pressure or downstream pitot pressure. In addition, it was found that extending even the off-axis probe too far from the base into the recirculation region into the vicinity of the rear stagnation point greatly disturbs the stagnation temperature profile at a station in the supersonic near wake.
- Fluid Mechanics