Transonic Flow about Two-Dimensional Airfoils by Relaxation Procedures

Abstract

A successive over-relaxation procedure has been developed to treat the inviscid, fully nonlinear, potential equations governing compressible flow. The procedure is designed to compute embedded shock waves and adjust to the Kutta condition during the course of the iterations. Adjustment to the Kutta condition, convergence rate control and other data handling are accomplished in a practical fashion by means of interacting graphics provided by a cathode-ray tube coupled to the computer. The procedure has been applied to blunt-nosed, lifting airfoils in a subsonic freestream. Calculated results are compared to exact theories and experiment.