Wall Interference on Airfoils in Transonic Tunnels at Mach One

摘要

A new approximate technique for determining the transonic flow about nonlifting airfoils at Mach 1 is introduced. The technique is based on combining the method of local linearization with an integral method. This combined technique is flexible enough to permit analysis of an airfoil in a transonic wind tunnel in order to determine wind tunnel wall interference effects at Mach 1. The results of carrying out such an analysis indicate that the interference will be negligible whenever a particular condition is satisfied-involving the blockage, the ratio of specific heats, the semi height of the tunnel, and the chord of the airfoil. (Author Modified Abstract)