벽면효과를 고려한 후퇴익 주위의 3차원 초음속 유동장에 관한 연구

Abstract

Numerical Analysis of Three Dimensional Supersonic Flow over Sweepback Wing with Wall Effect

by Kim, Tae-Hoon Advisor : Prof. Kim, Jae-Soo, Ph. D. Department of Aerospace Engineering, Graduate School of Chosun University

The supersonic flow around sweep back wings was investigated by two- and three-dimensional numerical analysis using the Reynolds-Averaged Navier-Stokes(RANS) equation with the Wilcox's turbulence model. The 2nd-order upwind TVD scheme based on the flux vector split using Van Leer's limiter was used as the numerical method. Numerical calculations were performed by the parallel processing with time discretizations carried out by the 4th-Order Runge-Kutta method. The taper ratio of wing is 0.6 for the sweep back wings. The Mach number and the Reynolds number were and , respectively. Pressure Coefficient() for the two-dimensional airfoil flow was compared with the reference literature[1]. And Airfoil's Pressure Coefficient() when the angle of attack(AOA) was 0.0° computed, the first case of the three-dimensional wing at the angle of attack(AOA)'s 0.0° and considering the wall effect condition was computed the Pressure Coefficient(). Second case of the three-dimensional wing at the angle of attack(AOA)'s 0.0° and ignore wall condition was computed the Pressure Coefficient(). And Third case of the three-dimensional wing at the angle of attack(AOA)'s 4.0°, 10.0° and considering the wall effect condition was computed the Pressure Coefficient(). The analysis cases of the three-dimensional wing are 6.