Abstract
A rapid expansion of moist air or steam in a supersonic nozzle gives rise to nonequilibrium condensation phenomena. Thereby, the nozzle flow is affected by the latent heat released by condensation of water vapor. Many papers for the passive control of shock-boundary layer interaction using the porous wall with a plenum underneath have been reported on the application of the technique to transonic airfoil flows. In this paper, this passive technique is applied to a steady condensation shock wave generated in a supersonic nozzle. For the effect of the passive shock-boundary layer control on steady condensation shock, Navier-Stokes equations were solved numerically using a 3rd-order MUSCL type TVD finite-difference scheme with a second-order fractional-step for time integration. As a result, the state of flow field has been clarified.
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