Study of unsteady flow field over a forward-looking endoatmospheric hit-to-kill interceptor
Author:
Affiliation:
1. CFD Research Corp., Huntsville, AL
2. BDM Engineering Services Co., Huntsville, AL
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1993-501
Reference24 articles.
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2. R.L. Stallings and P.B. Burbank. "Heat Transfer and Pressure Measurements on a Concave-Nose Cylinder for a Mach Number Range of 2.09 to 4.44," NASA TM-X-221,1959.
3. R.Bastianon,"SteadyandUnsteadySolutionofthe Flow Field Over Concave Bodies in Supersonic FreeStream,"AIAAPaper 68-946,ElCenuo,CA, 1968.
4. Supersonic Flow over Convex and Concave Shapes with Radiation and Ablation Effects
5. Approximate Riemann solvers, parameter vectors, and difference schemes
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2. Numerical simulation of viscous flow for hypervelocity projectiles and intercepters with nose cavity;32nd Aerospace Sciences Meeting and Exhibit;1994-01-10
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