Hypersonic jet control effectiveness

Investigation of fluidic thrust vectoring for scramjets

“…2 Flowfield around the injector with a hypersonic crossflow rapidly when small amount of injection are provided, tailing-off at higher injection pressures. As expected based on investigation 2D flat plates (Kumar et al 1997), the separation distance is largely independent of freestream Reynolds number. Results for both internal and external nozzles are comparable; however, there is suggestion that the internal exhaust tends to produce a marginally shorter separation distance.…”

Drag Estimation on Wedge-Shaped Protuberances in High-Speed Flows

“…Here the upstream separation causes an effective shock wave detachment (separation shock), lambda shock interactions, and a large shock-induced bow vortex. If the wedge is wide enough, the flow experienced by the forward face will correspond with that seen with the supersonic flow past a 2D ramp compression corner, which has been extensively studied [9][10][11][12][13][14][15][16]. Figure 1 presents the flow structure typically seen in the interaction of an oncoming boundary layer with a ramp compression corner, where the adverse pressure gradient imposed by the ramp deflection causes an upstream separation and an associated separation shock wave and underlying separation bubble, together with a second shock wave associated with reattachment of the separated shear layer.…”

“…Ten different wedge fairing configurations were tested, as listed in Table 1. Wedge angles of 25°(below the incipient separation wedge angle for a turbulent interaction [15]) and 40°were chosen, along with four span lengths, while the overall length and height of the model was kept constant. The principal dimension of interest in this study was therefore the span, or aspect ratio, of the wedge.…”