Boundary Layer Transition Measurements Using a Surface Hot Film Downstream of Distributed Roughness at Mach Numbers from 1·3 to 4·0
- 1 February 1965
- journal article
- research article
- Published by Cambridge University Press (CUP) in Journal of the Royal Aeronautical Society
- Vol. 69 (650) , 96-100
- https://doi.org/10.1017/s0001924000060358
Abstract
Summary: A surface hot film was used as a boundary layer transition indicator on wind tunnel models at Ifiach numbers from 1·3 to 4·0. The results illustrate the difficulty of fixing transition with distributed roughness on small models at supersonic speeds.Keywords
This publication has 3 references indexed in Scilit:
- Boundary-Layer Transition at Supersonic Speeds - Three-Dimensional Roughness Effects (Spheres)Journal of the Aerospace Sciences, 1962
- Effects of slight nose bluntness and roughness on boundary-layer transition in supersonic flowsJournal of Fluid Mechanics, 1962
- Heat-Transfer Characteristics of Hot-Film Sensing Element Used in Flow MeasurementJournal of Basic Engineering, 1960