Determination of the effect due wall interference on the flow around airfoil in the T-128 wind tunnel

Within the framework of linear subsonic theory, the problem of determining the effect due to wall interference on the flow around airfoil according to the pressure distributions measured on the airfoil and on the wind-tunnel test section walls is solved. For the test case (testing a BGK1 airfoil in the IAR1.5m wind tunnel), we compared the wall interference corrections to freestream Mach number and airfoil angle-of-attack that were obtained using our method and in the works by other authors. For an OSPB-77 airfoil model tested in the T-128 wind tunnel for two values of wall permeability, f = 0 and 3 %, corrections to distributed data and integral loads were applied in the range of Mach numbers from 0.2 to 0.78. The application of those corrections has made it possible to bring the results for f = 0 and f = 3 % in closer agreement up to the angles of attack at which flow separation occurs on the airfoil.