Computation of supersonic flow fields about bodies in coning motion using a shock-capturing finite-difference technique
- 17 January 1972
- proceedings article
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 1 reference indexed in Scilit:
- Laminar Boundary Layer on a Spinning Cone at Small Angles of Attack in a Supersonic FlowJournal of the Aeronautical Sciences, 1957