Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane tapered wing of aspect ratio 3.1 with 3 percent thick rounded nose section

John C. Heitmeyer
Jul 1952

A wing-body combination having a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.60 to 0.92 and from 1.20 to 1.90 at Reynolds numbers of 1.5 million, 2.4 million, and 3.8 million. (At a Reynolds number of 3.8 million the maximum test Mach number was limited to 1.70 because of wind-tunnel power imitations.)

An Adobe Acrobat (PDF) file of the entire report: