For flow over a two-dimensional ramp compression corner case, an experimental investigation to determine the incipient separation was carried out at Mach numbers between 0.55 and 0.9 and Reynolds numbers (based on undisturbed boundary layer thickness) between 350000 and 690000. Detailed surface pressure, pitot traversing and oil flow data were obtained for each ramp angle case. Two-dimensionality of the ramp compression corners was verified by the surface oil flow. A major finding of this study is that the incipient separation ramp angle is relatively independent of Mach number and Reynolds number within the range studied. The incipient separation ramp angle was found to be about 22.5 degrees.
Experimental study on high subsonic turbulent flow incipient separation
Experimentelle Studie der angehenden Abloesung bei Unterschallstroemungen mit grossen Turbulenzen
US Government Reports ; 1-63
1976
63 Seiten
Report
English
Incipient Turbulent Separation Induced by Swept Shock Waves
British Library Conference Proceedings | 1994
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