Determination of the influence of flow boundaries on the flow around airfoil in the T-128 wind tunnel
S.A. Glazkov, A.V. Semenov
Central Aerohydrodynamic Institute, Zhukovskii, Russia
Keywords: airfoil, induction of flow boundaries, blockage, flow angularity, slot permeability
Abstract
Within the framework of the linear subsonic theory, the problem of influence of flow boundaries on the flow around airfoil according to the measured distribution of pressures on the airfoil and on the test-section walls is solved. For the test case (testing a BGK1 airfoil in the IAR1.5m wind tunnel), we compared the corrections to the oncoming-flow Mach number and to the airfoil angle of attack that were obtained using our method and in works by other authors. For a OSPB-77 airfoil model tested in the T-128 wind tunnel for two values of wall permeability, ƒ = 0 and 3 %, correction of distributed data and integral loads was applied in the range of Mach numbers from 0.2 to 0.78. The application of corrections has made it possible to bring the results for ƒ = 0 and ƒ = 3% in closer agreement up to the angles of attack at which flow separation occurs on the airfoil.
|
