Numerical Study On The Effect Of Non-Equilibrium Condensation On Drag Divergence Mach Number In A Transonic Moist Air Flow

In the present study, the effects of non-equilibrium condensation on the drag divergence Mach number with the angle of attack in a transonic 2D moist air flow of NACA0012 are investigated using the TVD finite difference scheme. For the same a, the maximum upstream Mach number of the shock wave, Mmax, and the size of supersonic bubble decrease with the increase in Phi(0). For the same M-infinity, Phi(0), and T-0, the length of the non-equilibrium condensation zone Delta(z) decreases with increasing Phi(0). On the other hand, because of the attenuating effect of non-equilibrium condensation on wave drag, which is related to the interaction between the shock wave and the boundary layer, the drag coefficient C-D decreases with an increase in Phi(0) for the same M-infinity and a. For the same a, M-D increases with increasing Phi(0), while M-D decreases with an increase in a.