Abstract
Characteristics of transonic flow over an airfoil are determined by a shock wave standing on the suction surface. In this case, the shock wave/boundary layer interaction becomes complex because an adverse pressure gradient is imposed by the shock wave on the boundary layer. Several types of passive control techniques have been applied to shock wave/boundary layer interaction in the transonic flow. Furthermore, possibilities for the control of flow fields due to non-equilibrium condensation have been shown so far and in this flow field, non-equilibrium condensation occurs across the passage of the nozzle and it causes the total pressure loss in the flow field. However, local occurrence of non-equilibrium condensation in the flow field may change the characteristics of total pressure loss compared with that by non-equilibrium condensation across the passage of flow field and there are few for researches of locally occurred non-equilibrium condensation in a transonic flow field. The purpose of this study is to clarify the effect of locally occurred non-equilibrium condensation on the shock strength and total pressure loss on a transonic internal flow field with circular bump. As a result, it was found that shock strength in case with local occurrence of non-equilibrium condensation is reduced compared with that of no condensation. Further, the amount of increase in the total pressure loss in case with local occurrence of non-equilibrium condensation was also reduced compared with that by non-equilibrium condensation across the passage of flow field.
Highlights
A shock wave standing on the suction surface of airfoils determines the characteristics of transonic flow field
Several types of passive control techniques have been applied to shock wave/boundary layer interaction in the transonic flow
Local occurrence of non-equilibrium condensation in the flow field may change the characteristics of total pressure loss compared with that by non-equilibrium condensation across the passage of flow field and there are few for researches of locally occurred non-equilibrium condensation in a transonic flow field
Summary
A shock wave standing on the suction surface of airfoils determines the characteristics of transonic flow field In this case, the shock wave imposes an adverse pressure gradient on the boundary layer and it makes the shock wave/boundary layer interaction complex. Bahi et al [1] and Raghunathan [2] described that a porous wall and cavity system that applied at the foot of the shock wave was effective in decreasing undesirable adverse pressure gradient of the shock wave/boundary layer interaction. This control method essentially leads to large viscous losses caused by the porous walls. Raghunathan [4] and O'Rourke et al [5] reported that the passive control using the porous wall with a cavity and vortex control jets upstream of porous wall might be effective control method for the shock position and pressure gradient
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