The results of an investigation into the effects that sub-boundary layer vortex generators (SBVGs) have on reducing normal shock-induced turbulent boundary-layer separation are presented. The freestream Mach number and Reynolds number were M = 1·45 and 15·9 x 10 6 /m, respectively. Total pressure profiles, static pressure distributions, surface total pressure distributions, oil flow visualisation and Schlieren photographs were used in the results analysis. The effects of SBVG height, lateral spacing and location upstream of the shock were investigated. A novel curved shape SBVG was also evaluated and comparisons against the conventional flat vane type were made. The results show that in all but two cases, separation was completely eliminated. As expected, the largest SBVGs with height, h = 55%δ, provided the greatest pressure recovery and maximum mixing. However, the shock pressure rise was highest for this case. The experiments showed that the mid height SBVG array with the largest spacing provided similar results to the SBVG array with the largest height. Reducing the distance to shock to 10δ upstream also showed some improvement over the SBVG position of 18δ upstream. It was suggested that total elimination of the separated region may not be required to achieve a balance of improved static pressure recovery whilst minimising the pressure rise through the shock. The effect of curving the SBVGs provided an improved near wall mixing with an improved static and surface total pressure recovery downstream of the separation line. The optimum SBVG for the current flow conditions was found to be the curved vanes of h = 40%δ, with the largest spacing, located at 18δ upstream of the shock. Overall, it was apparent from the results that in comparison to larger vortex generators with a height comparable to δ, for SBVGs the parameters involved become more important in order to obtain the highest degree of mixing from a given SBVG configuration.
u δ streamwise velocity at edge of boundary layer u τ x streamwise co-ordinate relative to shock wave location [m] y vertical distance from wall y + Δ boundary-layer thickness [mm] and is defined as a vertical distance at which the x-component of the velocity reaches 99·5% of the free-stream velocity distance of SBVG upstream of shock in terms of δ ρ air density τ w wall skin friction v air kinematic viscosity
In a number of applications, turbulent boundary layers are exposed to a gradual or rapid acceleration. As a result of this, the flow may change to a laminarised state before retransitions again to a turbulent flow. This change of state (turbulent-laminar-turbulent) can have drastic effects on a variety of engineering problems. For example it has significant effects on the heat transfer rate at a boundary over which it is flowing, the mixing of fuel and air in the scramjet combustors, the mixing process in the wake of a transonic turbine blade and hence the base drag, etc.
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