Shock tube test time limitation due to turbulentwall boundary layer
Open Access
- 1 January 1964
- journal article
- research article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 2 (1) , 84-93
- https://doi.org/10.2514/3.2218
Abstract
No abstract availableKeywords
This publication has 9 references indexed in Scilit:
- Test Time in Low-Pressure Shock TubesPhysics of Fluids, 1963
- Testing Time and Contact-Zone Phenomena in Shock-Tube FlowsPhysics of Fluids, 1961
- On Flow Duration in Low-Pressure Shock TubesPhysics of Fluids, 1960
- Boundary-Layer Transition and Heat Transfer in Shock TubesJournal of the Aerospace Sciences, 1960
- Shock-Tube Performance at Low Initial PressurePhysics of Fluids, 1959
- Shock-Tube Testing TimeJournal of the Aerospace Sciences, 1959
- An Experimental Study of the Turbulent Boundary Layer Behind the Initial Shock Wave in a Shock TubeJournal of the Aerospace Sciences, 1958
- Stagnation Point Heat-Transfer Measurements in Dissociated AirJournal of the Aerospace Sciences, 1958
- The wall boundary layer behind a moving shock wavePublished by Springer Nature ,1958