Interactions Between Wholly Laminar or Wholly Turbulent Boundary Layers and Shock Waves Strong Enough to Cause Separation
- 1 November 1953
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of the Aeronautical Sciences
- Vol. 20 (11), 729-739
- https://doi.org/10.2514/8.2826
Abstract
No abstract availableThis publication has 4 references indexed in Scilit:
- The measurement of skin friction in a turbulent boundary layer at a Mach number of 2.5, including the effect of a shock-waveProceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences, 1952
- A Mixing Theory for the Interaction Between Dissipative Flows and Nearly Isentropic StreamsJournal of the Aeronautical Sciences, 1952
- Characteristics of the Turbulent Boundary Layer on a Flat Plate in Compressible Flow from Measurements of Friction in PipesJournal of the Aeronautical Sciences, 1950
- Aerodynamic TheoryPublished by Springer Nature ,1935