Abstract
The transonic flow over an airfoil is characterized by a shock wave standing on the suction surface. When non-equilibrium condensation occurs in a supersonic flow field, the flow is affected by latent heat released by it. According to previous works, it was found that the occurrence of non-equilibrium condensation just before the shock wave led to reduction of shock strength. In these studies, 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 the nozzle 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 local occurrence of non-equilibrium condensation on transonic flow field with a circular bump. As a result, shock strength and total pressure loss decrease with a decrease of generation region of condensate droplets.
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