Analysis of four wall flow control in supersonic duct using ramped-vanes micro vortex generator

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Analysis of four wall flow control in supersonic duct using ramped-vanes micro vortex generator

Nishantt, N. / Baraiya, Nikhil A.

Shock induced flow separation causes poor pressure recovery in the inlets of the ramjet and scramjet engine, leading to a phenomenon called unstart. A passive control technique involving ramped vane micro vortex generator is used for alleviating flow separation and improving pressure recovery. In this paper, two different inlet pressure giving rise to two different shock locations is numerically studied using RANS based k-omega SST model. The flow control using a ramped vane micro vortex generator is applied on four walls and the height of the passive device is changed to visualize its effect on the flow separation pattern at the bottom wall, static pressure recovery on all the walls and the exit stagnation pressure ratio at the outlet. For device height 0.35δ, the case with three ramp configuration at the bottom wall shows a reduction in separation bubble length and steepening of pressure recovery. Whereas, for device height 0.52δ, the case with four ramp configuration at the bottom wall showed full centerline flow and enhanced corner separation for shock location at 37 mm from the trailing edge of the RV MVG. Also, the exit stagnation pressure ratio is recovered better when the device is kept near the shock location.