An investigation of inviscid supersonic nozzle flow with condensation has been carried out using the finite difference method. In the present paper, equations of the condensation theory have been solved simultaneously with the gas dynamic equations in the case of homogeneous condensation of moisture air in a steady and two-dimensional supersonic circular type nozzle. For the gas dynamic equations, interior points are computed using a second-order accurate, noniterative, and implicit procedure, while all boundary points are computed by a left running characteristic method. The mass fraction of the condensate is integrated along the streamlines selected between the nozzle wall and centerline by using the Runge-Kutta with Gill's coefficients. The calculated values of static pressure ratio are a little smaller than those of the experimental results in the region of the downstream along the centerline. Based on the results, the effect of homogeneous condensation on the flow fields has been clarified.
