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- W2006448714 abstract "Large-eddy simulations of a vortex generator embedded upstream of a normal shock boundary-layer interaction followed by a subsonic diffuser were conducted. In particular, the “ramped-vane” flow control devicewas placed in a supersonic boundary layer with a freestream Mach number of 1.3 and a Reynolds number of 2400 based on momentum thickness. The ramped vane had a height of 0:52 and generated strong streamwise vorticity that entrained the high-momentum flow to the near-wall region. This contributed to decreasing the shock-induced flow separation while significantly increasing the skin friction coefficient in the diffuser where a strong adverse pressure gradient was present. In addition, it was found that the high-momentum flow persisted far downstream of the shock interaction region, which yielded reductions of both the displacement thickness and the shape factors compared to the uncontrolled case." @default.
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- W2006448714 date "2012-10-01" @default.
- W2006448714 modified "2023-09-25" @default.
- W2006448714 title "Impact of Ramped Vanes on Normal Shock Boundary Layer Interaction" @default.
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- W2006448714 doi "https://doi.org/10.2514/1.j051253" @default.
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