EXPERIMENTAL-VERIFICATION OF A WALL INTERFERENCE CORRECTION METHOD WITH INTERFACE MEASUREMENTS

A wall interference assessment and correction method for two-dimension al subsonic wind-tunnel testing is presented. Pressure coefficient and angle-of-attack correction are calculated using velocity measurements on interfaces inside the wind tunnel. A mathematical representation o f the test article and tunnel wall boundary conditions is not required . Available experimental data of an NACA 0012 airfoil tested at a Mach number of 0.70 and at two different angle of attack in a solid wall w ind tunnel are applied to the method. Blockage corrections are compute d and corrected surface pressure coefficients compare favorably to fre e-air flowfield data if the tunnel flowfield is subsonic. The present wall interference correction method can determine blockage corrections in transonic wind-tunnel flowfields with restrictions. The computed a ngle-of-attack correction is negligible for the given experimental dat a.