An Experimental Determination of Flat Plate Recovery Factors for Mach Numbers Between 1.90 and 3.14
- 1 November 1954
- journal article
- research article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of the Aeronautical Sciences
- Vol. 21 (11), 763-771
- https://doi.org/10.2514/8.3200
Abstract
No abstract availableThis publication has 2 references indexed in Scilit:
- Boundarv-Layer Stability and Transition in Subsonic and Supersonic FlowJournal of the Aeronautical Sciences, 1953
- Plattenthermometer in Strömung mit großer Geschwindigkeit und turbulenter GrenzschichtForschung im Ingenieurwesen, 1942