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
Laser photography of hypervelocity projectiles
| Engineering Index Backfile | 1965
Hypervelocity projectiles boost defensive systems
| Tema Archiv | 1990
Depth of penetration of hypervelocity projectiles
| AIAA | 1965
Fragmentation of hypervelocity aluminum projectiles on fabrics
| Online Contents | 2012