Inviscid flow fields have been computed for blunt axisymmetric shapes exposed to a hypersonic environment. A fully implicit scheme using a flux vector splitting technique was used to obtain a finite difference formulation. To increase computational efficiency, an approximate factorization scheme was used. Flow-field solutions were obtained for chemically reacting air using a decoupled approach. Flow fields were computed for blunted, flared shapes over a range of Mach numbers from 2 to 20.
Inviscid Flow Field Computation of Hypervelocity Projectiles
Sae Technical Papers
Aerospace Technology Conference and Exposition ; 1988
01.10.1988
Aufsatz (Konferenz)
Englisch
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