A detailed investigation of attached supersonic turbulent boundary layers over an extensive range of Reynolds numbers (12 millions to 314 millions) is presented. Experimental measurements were obtained for adverse pressure gradients ranging in magnitude from those of previous investigations to those approaching separation. The measurements include mean values of surface pressure and skin-frictiom, mean-flow profiles, and profiles of the three turbulent velocity fluctuation components and turbulent shear stress. Numerical solutions, employing three turbulence models of various degrees of complexity have been compared with the details of the measured flow fields. Generally, it was found that the more sophisticated turbulence models are superior to a mixing length model for predicting the Reynolds number and pressure gradient effects. However, some details of the turbulent fluctuations as well as the exact Reynolds number trends indicated by the data were not accurately predicted with any of the turbulence models considered. (DePo)
Reynolds number and pressure gradient effects on compressible turbulent boundary layers
Wirkung der Reynolds Zahl und des Druckverlaufes auf kompressible, turbulente Grenzschichten
AIAA-Papers ; 1-16
1978
16 Seiten, 25 Bilder, 1 Tabelle, 29 Quellen
Aufsatz (Konferenz)
Englisch