Abstract
Steady two-dimensional flow of vapor/carrier gas mixtures (moist air) with nonequilibrium condensation is investigated in theory and experiment. Aside from Laval nozzles, transonic flow over airfoils at M<x ^ 1 is considered. The numerical calculation is based on the Euler equation linked with the classical theory of homogeneous nucleation and droplet growth using a new diabatic, time-dependent, explicit, finite volume method. By means of this model, the effects of energy supply in local supersonic flow over airfoils are investigated including a detailed analysis of the two-dimensional structure in the diabatic case. The variation of the pressure drag coefficient due to the heating is the sum of the following connected processes: the reduction of the wave drag in the local supersonic area producing a higher Mach number behind the shock, the shock shifting, and the pressure increase in the rear section of an airfoil due to evaporation. Both airfoil series investigated, circular arc and NACA-0012, show the same tendency concerning the shifting of the normal shock. But the pressure drag coefficients vary in opposite directions with different supply conditions.
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