Mach 8 to 22 studies of flow separations due to deflected control surfaces
- 1 February 1964
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 2 (2), 312-321
- https://doi.org/10.2514/3.2289
Abstract
No abstract availableThis publication has 2 references indexed in Scilit:
- Some Experiments on Hypersonic Separated FlowsARS Journal, 1962
- Sweepback Effects in Turbulent Boundary-Layer Shock-Wave InteractionJournal of the Aerospace Sciences, 1960