Transonic flow around airfoils with relaxation and energy supply by homogeneous condensation

Steady 2-D flow of vapor/carriergas mixtures (moist air) with nonequilibrium condensation is investigated in theory and experiment. Aside from Lava1 nozzles, transonic flow over airfoils at (Formula Presented) 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 inciuding a detailed analysis of the 2-D structure in the diabatic case. The variation of the pressure drag coefficient due to the heating is the sum of three connected processes: the reduction of the wave drag in the local supersonic area, the shockshifting, andthe pressure decrease in the rearsection due to evaporation. Both airfoil series investigated, circular arc and NACA-0012, show the same tendency concerning theshiftingof the normalshock. Butthepressuredragcoefficients vary in opposite directions with different supply conditions.