Abstract: A wall-signature method for wall interference assessment and / or correction in high speed wind tunnel 3-dimensional model tests is presented. The method considers that the flow near tunnel walls is subcritical while the flow near model may be supercritical and shock waves may exist near by model. It can be used for various ventilated wall or solid wall wind tunnel tests in subsonic or transonic ranges. More than twenty test cases including four models in three different tunnels are corrected by this method. The corrected results coninside well with the results of NASA nonlinear method.

Key words: wind tunnel test, wall interference, transonic flow