Aerodynamic Characteristics at Subsonic and Supersonic Mach Numbers of a Thin Triangular Wing of Aspect Ratio 2

Résumé du livre

This report presents the results of a wind-tunnel investigation conducted to determine the effects of Mach number on the aerodynamic characteristics of a wing of triangular plan form. The wing was of aspect ratio 2 and of symmetrical double-wedge section with 5-percent chord maximum thickness at 20 percent of the chord. The tests were conducted at Mach numbers from 0.50 to 0.975 and 1.09 to 1.49 and at Reynolds numbers ranging from 0.67 to 0.85 million.