Calculation of Unsteady Transonic Flows with Shocks by Field Panel Methods

摘要

A field panel method, FTRAN2, for the calculation of two-dimensional inviscid transonic flow, including shock waves about an oscillating wing, is presented. For a NACA 64A006 and a NACA 64A010 airfoil, results are presented and compared with results of finite difference methods. The good agreement obtained and the lower computer cost show the feasibility of the method. A modification of FTRAN2, applicable to three dimensions, and which achieves further reduction of the computational effort is proposed. Results for an oscillating flat plate are satisfactory.