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Flowfield calculations past an entry probe with ablated nose shape (1980)

Wellmuenster, K. J. ; Kumar, A. ; Graves, R. A., Jr.

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Publication Date: 2011-08-17

Description: The effects of ablated nose shapes on the flowfield solutions are studied, using a time-dependent finite-difference method developed by Kumar, et al. (1979). Solutions are obtained for the laminar flow of a radiating mixture of H-He in chemical equilibrium past a blunt axisymmetric body at zero angle of attack. The freestream conditions correspond to a point on a typical Jovian entry trajectory, and the initial probe shape is a 45-deg half-angle spherically blunted cone. It is found that as nose bluntness increases, the following occur: in the nose region, shock standoff distances and radiative heating rates increase substantially; surface pressure level increases, but convective heating rates decrease.

Keywords: AERODYNAMICS

Type: AIAA Journal; 18; June 198

Format: text

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