Numerical Solution of Supersonic Viscous Flow over Blunt Delta Wings
Author:
Affiliation:
1. Iowa State University, Ames, Iowa
2. NASA Ames Research Center, Moffett Field, Calif.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Reference23 articles.
1. Viscous flow over a cone at moderate incidence—I
2. Calculation of the Flow on a Cone at High Angle of Attack
3. An implicit method for three dimensional viscous flow with application to cones at angle of attack
4. Calculation of supersonic viscous flow over delta wings with sharp subsonic leading edges
5. 5Lin, T. C. and Rubin, S. G. "A Numerical Model for Supersonic Viscous Flow Over a Slender Reentry Vehicle," AIAA Paper 79-0205, Jan.1979.
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