Abstract Experiments were performed to investigate a transonic, turbulent boundary layer over a bi-convex corner. The total turning angle η ranged from 10 deg to 17 deg. In subsonic expansion flows, the presence of a bi-convex corner results in a decrease in local peak Mach number and the amplitude of peak surface pressure fluctuations . There is a delay in transition from subsonic to transonic expansion flows. A dual expansion is observed in transonic expansion flows. Shock structure, boundary-layer separation and were dependent on freestream Mach number M, first turning angle and η. The length of the first corner also plays an important role. An increase in results in less flow expansion, while a decrease in the amplitude of is associated with a shorter .
Investigation of transonic bi-convex corner flows
Aerospace Science and Technology ; 39 ; 22-30
2014-08-27
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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