Experiments were performed to study two compression corner interactions at Mach 7.2 and at a Reynolds number based on a momentum thickness of 3500. Turning angles were selected such that the flow remained attached for the lower 8° case and a large separation bubble formed for a higher 33° case. The measurements were performed using particle image velocimetry, allowing an examination of both changes in the mean flow as well as turbulence in the near field of the interaction. Results were interpreted while closely considering the fidelity of the tracer particle response, which was seen to vary strongly throughout the flow. Upstream of the interaction, the particle response was seen to be insufficient to resolve the wall-normal component of turbulence, as in previous studies. Downstream of the interaction, the increased fluid viscosity raised the particle response such that measurements of wall-normal turbulence compared favorably with direct numerical simulations and large-eddy simulations at matching conditions. The streamwise turbulence intensities were seen to be relatively unaffected by the 8° interaction, but they displayed strong amplification across the 33° interaction. The wall-normal velocity fluctuations and Reynolds shear stresses were strongly amplified in both cases. Surprisingly, the return to equilibrium downstream of the shock was approached much more rapidly in the 33° case.
Experimental Investigation of Two Hypersonic Shock/Turbulent Boundary-Layer Interactions
AIAA Journal ; 56 , 12 ; 4830-4844
2018-11-09
15 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Hypersonic crossing shock-wave/turbulent-boundary-layer interactions
Tema Archiv | 1993
|