An Experimental Study of the Turbulent Boundary Layer Behind the Initial Shock Wave in a Shock Tube
- 1 October 1958
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of the Aerospace Sciences
- Vol. 25 (10) , 644-652
- https://doi.org/10.2514/8.7818
Abstract
No abstract availableKeywords
This publication has 2 references indexed in Scilit:
- Use of the Shock Tube Wall Boundary Layer in Heat Transfer StudiesJournal of Jet Propulsion, 1956
- Transition Through a Contact RegionJournal of Applied Physics, 1955