Transonic Navier-Stokes solutions about a generic hypersonic configuration
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Virginia 23665
2. Vigyan, Inc., Hampton, Virginia 23666
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.46038
Reference20 articles.
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2. The numerical simulation of transonic separated flow about the complete F-16A
3. 3Buning, P. G., Chiu, I. T., Obayashi, S., Rizk, Y. M., and Steger, J. L. "Numerical Simulation of the Integrated Space Shuttle Vehicle in Ascent," AIAA Paper 88-4359, Aug.1988.
4. Navier-Stokes solutions about the F/A-18 forebody-LEX configuration
5. 5Shrewsbery, G. D., Vadyak, J., Schuster, D. M., and Smith M. J. "Computation of Aircraft Component Flow Fields at Transonic Mach Numbers Using a Three-Dimensional Navier-Stokes Algorithm," NASA CP-3020, Vol. I, April 1988.
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1. Multiblock Navier-Stokes solutions about the F/A-18 wing-LEX-fuselage configuration;Journal of Aircraft;1993-05
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