Abstract
Flow separation control stragies on contour bump models under a Mach 1.3 freestream has been investigated experimentally in a transonic/supersonic wind tunnel. Surface oil flow visualisaiton, Schlieren photography, and Particle Image Velocimetries (PIV) measurements have been conducted. Flow separation, in both streamwise and spanwise directions, was observed at the valley of the plain contour bump. Usage of passive by-pass jets on contour bump show no effects in reducing the extent of flow separation in both streamwise and spanwise directions. It is observed that both spanwise and streamwise flow separation are reduced by blowing jets from the valley of the contour bump. It is believed that the jets hinder the formation of the spanwise, counter-rotating vortrices and deflect the shear layer to make the flow at the valley becomes more attach to the surface of the bump. Two active jet pressures of 1 bar and 4 bar have been employed in this study. It is observed that a higher jet pressure is more effective in achieving flow separation control in both streamwise and spanwise directions. Further investigations will be conducted to obtain surface pressure profiles on the contour bump models.
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