Computational design of low aspect ratio wing-winglets for transonic wind-tunnel testingA computational design has been performed for three different low aspect ratio wing planforms fitted with nonplanar winglets; one of the three planforms has been selected to be constructed as a wind tunnel model for testing in the NASA LaRC 7 x 10 High Speed Wind Tunnel. A design point of M = 0.8, CL approx = 0.3 was selected, for wings of aspect ratio equal to 2.2, and leading edge sweep angles of 45 and 50 deg. Winglet length is 15 percent of the wing semispan, with a cant angle of 15 deg, and a leading edge sweep of 50 deg. Winglet total area equals 2.25 percent of the wing reference area. This report summarizes the design process and the predicted transonic performance for each configuration.
Document ID
19890038138
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kuhlman, John M. (West Virginia Univ. Morgantown, VA, United States)
Brown, Christopher K. (West Virginia University Morgantown, United States)