FLIGHT AND WIND-TUNNEL INVESTIGATIONS ON BOUNDARY-LAYER-TRANSITION

Flight and wind-tunnel experiments have been carried out to measure the pressure distribution and the transition location on a special wing glove. By means of the linear stability theory of laminar boundary layers limiting N values of Tollmien-Schlichting waves at the transition location have been evaluated. The values of N ≈ 13.5 are nearly independent of Reynolds number and are the same in flight and wind-tunnel tests. © 1989 by DLR. © The American Institute of Aeronautics and Astronautics, Inc. All rights reserved.