Floating shock fitting for three-dimensional inviscid supersonic flows
Author:
Affiliation:
1. National Aerospace Laboratory, Tokyo, Japan
2. Institute of Space and Astronautical Science, Tokyo, Japan
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Reference22 articles.
1. Computation of nonequilibrium three-dimensional inviscid flow over blunt-nosed bodies flying at supersonic speeds
2. Supersonic Flow about Slab Delta Wings and Wing-Body Configurations
3. 4Kutler, P., Reinhardt, W. A., and Warming, R. F. "Multi-Shocked Three Dimensional Supersonic Flowfields with Real Gas Effects,'M/>4/4 Journal, Vol.11, May 1973, pp.657-664.
4. 5Solomon, J. M., Ciment, M., Ferguson, R. E., and Bell, J. B. "Inviscid Flowfield Calculations for Re-entry Vehicles with Control Surfaces,'MM,4 Journal, Vol.15, Dec. 1977, pp.1742-1749.
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