Heat transfer from hypersonic turbulent flow at a wedge compression corner
- 28 November 1972
- journal article
- research article
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 56 (4) , 741-752
- https://doi.org/10.1017/s0022112072002630
Abstract
A hypersonic gun tunnel has been used to measure the heat-transfer-rate distribution over a compression corner under turbulent boundary-layer conditions. Attached, incipient and separated flows are considered. The results are compared with other experimental data and with the predictions of a simple theory.Keywords
This publication has 2 references indexed in Scilit:
- Seven Ironies of Philosophy for Peace, from Ferré to Fackenheim: Review ArticleStudies in Religion/Sciences Religieuses, 1971
- A Particular Solution to the Turbulent-Boundary-Layer EquationsJournal of the Aerospace Sciences, 1960