Abstract: The correction method uses the static pressures measured near the tunnel walls during modeI tests as boundary conditions.It is required that the flow near the walls is subsonic and the freestream Mach number is less than 1.It is still valid when there are shock waves and supersonic pockets near the model as long as shock waves do not extend to walls and applicable to various ventilated wall or solid wall test sections. Corrections for three models tested abroad are in quite good agreement with NASA’s resuIts,which are obtained by a non-linear correction method.The present method has been applied to B737 model tested in CARDC 1.2m wind tunnel.The results show that this method is applicable to transonic wall interference correction for highaspect-ratio airplane tests.

Key words: aerodynamic interference, transonic wind tunnels, wall pressure, data reduction