Flow phenomena and separation over delta wings with trailing-edge flaps at Mach 6.
- 1 December 1968
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 6 (12) , 2380-2387
- https://doi.org/10.2514/3.4998
Abstract
No abstract availableKeywords
This publication has 4 references indexed in Scilit:
- Turbulent heat transfer associated with control surface at Mach 6.AIAA Journal, 1968
- Boundary layer separation in hypersonic flowPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1966
- A study of the pressure and heat transfer distribution on highly swept slab delta wings in supersonic flowPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1966
- STUDIES OF HIGH LIFT/DRAG RATIO HYPERSONIC CONFIGURATIONSPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1964