Effect of non-equilibrium condensation on lift divergence Mach number at transonic speeds

다국어 초록 (Multilingual Abstract)

In the present paper, the effects of non-equilibrium condensation on the lift divergence Mach number with the angle of attack in a transonic2-D moist air flow of NACA0012 are investigated using a numerical analysis with a total variation diminishing scheme. In the caseof T0 = 298 K and α = 3°, the lift divergence Mach number Mld decreases with increasing Φ0 up to 40%, whereas beyond Φ0 = 40%, thelift divergence Mach number is nearly constant at Mld = 0.75. On the other hand, for the case of α = 6°, Mld increases with increasing Φ0up to 47%, and then Mld begins to decrease with an increase in Φ0. Because of the attenuating effect of non-equilibrium condensation onthe shock stall, for the case of α = 3°, CL generally decreases with an increase in Φ0, whereas for M∞ = 0.85, which is appreciably largerthan the lift divergence Mach number, CL increases with an increase in Φ0. In the case of M∞ = 0.85, regardless of Φ0, it is shown that thelocation of the maximum Mach number at the upper wall side is nearly constant at x/c = 0.4. It is found that the Mach number for theminimum CL decreases with an increase in Φ0.

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