LU 근사 인자화 기법을 이용한 항공기 날개 주위의 압축성 난류유동 해석

Abstract

A computer code incorporating a number of existing proper computational methods isdeveloped to investigate the three dimensional compressible turbulent flow around an aircraft wing. LU-factored implicit upwind TVD scheme is employed in which the Harken-Yee`s modified upwind scheme is used far the Explicit operator and the Steger-Warming splitting for the implicit part. Baldwin-Lomak turbulent model is adopted in this Computer Code. Flow past on NACA0012 airfoil and ONERA M6 wing are imputed under three different conditions. The flow around the ONERA M6 wing showed that the regults were in good agreement with the experimental data if the angle attack war less than 6 degrees.