A THEORETICAL INVESTIGATION OF THE HYPERSONIC AXISYMMETRIC NEAR WAKE RECOMPRESSION REGION.
AVCO EVERETT RESEARCH LAB EVERETT MASS
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The pressure distribution in the laminar, hypersonic, axisymmetric near wake of slender bodies is investigated. Implosion of the inner streamlines of the inviscid, rotational wake of the boundary layer produces a local maximum in the axial pressure distribution. Characteristicsstream tube calculations are presented which reproduce the observed axial pressure distributions, including the effect of variable Reynolds number. A scaling law is obtained which shows that the magnitude of the pressure maximum increases with decreasing Reynolds number the hypersonic interaction parameter is central to this correlation of experimental data. The effects of variable cone angle and free-stream MACH NUMBER UPON the calculated pressure distributions are easily accounted for. A critical point is shown to exist in the region of favorable pressure gradient, and a near wake uniqueness criterion is thereby deduced. Author
- Guided Missile Reentry Vehicles
- Fluid Mechanics