Investigation of Wing Characteristics at a Mach Number of 1.53. 2 - Swept Wings of Taper Ratio 0.5

摘要

Three component tests were conducted at a Mach number of 1.53 of seven wings varying in angle of sweep from 60 degrees sweepforward to 60 degrees sweepback. The wings had a uniform isosceles-triangle section 5 percent thick and a common taper ratio of 0.5. The range of sweep angles provided both supersonic and subsonic leading and trailing edges at the test Mach number. Measurements were made of lift, drag, and pitching moment at a Reynolds number of 0.75 million. The experimental results are analyzed and compared with characteristics calculated by means of linear theory. The experimental values of the lift-curve slope were found to agree reasonably with the theory over the complete range of sweep angles.