When condensation occurs in supersonic flow fields, the flow is affected by the latent heat released, and if the heat released exceeds a certain quantity, a condensation shock wave will occur There are many papers for the passive control of shock-boundary layer interaction using the porous wall with a plenum underneath on the application of the technique to transonic airfoil flows. In the present study, this passive technique is applied to the control of a steady condensation shock wave generated in a supersonic nozzle. In order to clarify the effect of the passive shockboundary layer control on 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 simulated flow fields were compared with experimental data in good agreement and the aspect of the flow field has been clarified. When condensation occurs in supersonic flow fields, and the heat release exceeds a certain quantity, a condensation shock wave will occur There are many papers for the passive control of shock-boundary layer interaction using the porous the wall with a plenum underneath on the application of the technique to transonic airfoil flows. In the present study, this passive technique is applied to the control of a steady steady shock wave generated in a supersonic nozzle. In order to clarify the effect of the the passive shockboundary layer control on 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 simulated flow fields were compared with experimental data in good agreement and the aspect of the flow field has been clarified.