Separated ShockWave/turbulent boundary layer interactions at hypersonic speeds

Collection of Technical Papers - 36th AIAA Fluid Dynamics Conference

Volumn 1, Issue , 2006, Pages 345-362

  Murray, N ^a   Hillier, R ^a,b  

^a IMPERIAL COLLEGE LONDON   (United Kingdom)

^b Department of Compressible Flow ^*

Author keywords

[No Author keywords available]

Indexed keywords

HEAT TRANSFER; HYPERSONIC FLOW; PRESSURE EFFECTS; REYNOLDS NUMBER; SHOCK WAVES; TURBULENT FLOW;

BENCHMARK INTERACTIONS; SEPARATED SHOCKWAVE/BOUNDARY LAYER INTERACTIONS (SWBLI); SURFACE PRESSURE TRANSFER;

BOUNDARY LAYERS;

EID: 33845238491     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.2514/6.2006-3038     Document Type: Conference Paper

References (5)

1. Needham D.A., Elfstrom G.M., S. J., "Design and operation of the Imperial College number 2 hypersonic gun tunnel," Aero Report 70-04, Imperial Collge London, 1970.
2. Cook W.J., Felderman E.J., "Reduction of data from thin film heat transfer gauges: a concise numerical technique," AIAA Journal, Vol. 4-3, 1966, pp. 561-562.
3. Murray N., Hillier R., "Hypersonic ShockWave/Turbulent Boundary Layer Interactions In A Three-Dimensional Flow," AIAA, Vol. AIAA-2006-0121, 2006.
4. Coleman G.T., Stollery J.L., "Heat transfer from hypersonic turbulent flow at a wedge compression corner," J. Fluid Mech, Vol. 56, part 4, 1972, pp. 741-752.
5. Chapman D.R., Kuehn D.M., Larson H.K., "Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition," NACA, Vol. 1356, 1958, pp. 421-460.