engleski

Viscous-Inviscid Interaction Method for Steady Transonic Flow

A numerical method for steady loads determination on airfoils in transonic flow with shock wave appearance is demonstrated. The method implements Euler equations for inviscid region and integral boundary layer equations for viscous region near airfoil. The viscous-inviscid interaction is implemented through transpiration velocity. Euler solution is calculated by applying Van Leer flux- vector splitting on body-fitted C-grid. The boundary layer model is calculated applying Drela’s model of integral boundary layer equations for laminar and turbulent flow. The transition is predicted by the e^n method. The viscous-inviscid interaction method is made in the direct mode. The method gave comparable results with the calculated RANS results and experimental data, while time and computational costs were slightly higher than for pure Euler calculations. The method predicted the position of shock wave slightly shifted toward trailing edge of airfoil with respect to the position obtained by experiment, but in front of RANS and Euler results.

viscous-inviscid coupling; transonic flow; airfoil; transpiration velocity

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