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Inviscid Flow Field Computation of Hypervelocity Projectiles
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English
Abstract
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.
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Hoffmann, K., Bertin, J., and Chiang, T., "Inviscid Flow Field Computation of Hypervelocity Projectiles," SAE Technical Paper 881520, 1988, https://doi.org/10.4271/881520.Also In
References
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