Description: Report presenting the results of an experimental wind-tunnel investigation of the damping in pitch of two triangular wings having leading edges swept back 45 degrees are presented. The wings differed only in airfoil section. Results regarding the damping coefficients, aeroelastic effects at supersonic speeds, Reynolds number effects, and application of the results to the prediction of the dynamic behavior of full-scale aircraft are provided.
Date: December 1, 1950
Creator: Tobak, Murray; Reese, David E., Jr. & Beam, Benjamin H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department