A Field Panel Method for the Calculation of Inviscid Transonic Flow About Thin Oscillating Airfoils with Shocks

摘要

A field panel method for two-dimensional flow, based on the solution on an integral equation which combines a subsonic lifting surface panel method with subsonic source panels in the flow is presented. These source panels account for nonuniformities in the velocity distribution due to airfoil thickness and incidence. For an NACA 64A006 and for an NACA 64A010 airfoil, transonic results are presented and compared with results of the LTRAN2-NLR code. The good agreement obtained shows the feasibility of the method. The lower computer cost makes this approach attractive for extension to three-dimensional flow.