미소교란 방정식을 이용한 천음속 유동장 해석

Abstract

The very efficient three-dimensional transonic unsteady aerodynamic code(TSD3KR) is developed. A time-accurate approximate factorization(AF) algorithm is formulated for the solution of the three-dimensional unsteady transonic small-disturbance equation. The AF algorithm consists of a Newton linearization procedure coupled with an internal iteration technique. A finite-difference method is used in the space discritizations and also Engquist-Osher difference method is applied to achieve the numerical stability in the strong shock wave region. The non-reflecting far-field boundary conditions is applied to eliminate the disturbed numerical errors reflected from the far-field boundaries. Present TSD3KR results are compared with experimental data and other analytical results for validation. The present steady and unsteady aerodynamic results show good agreement with the previous results for the various configuration wings.