摘要: An investigation has been conducted to determine the lift, drag, and pitching-moment characteristics of a cambered and twisted arrow wing and an uncambered and untwisted arrow wing. The cambered and twisted wing was designed to gi... 展开 An investigation has been conducted to determine the lift, drag, and pitching-moment characteristics of a cambered and twisted arrow wing and an uncambered and untwisted arrow wing. The cambered and twisted wing was designed to give a high value of maximum lift-drag ratio at a lift coefficient of 0.1 and at a Mach number of 2.50. Each wing had a leading-edge sweep of 74 deg., an aspect ratio of 1.6, a taper ratio of 0, and a notch ratio of 0.714. A 3-percent-streamwise biconvex thickness distribution was centered on the mean camber surface of both wings. Tests were conducted at Mach numbers from 1.6 to 2.8 through a range of angle of attack from -6 deg. to 14 deg. The Reynolds number based on mean aerodynamic chord was 5.0 x 10( exp 6) for all tests. The maximum lift-drag ratio at the design Mach number for the cambered and twisted wing was 7.85 and, thus, was below the theoretically predicted value of 9.10. In addition, the cambered and twisted wing had only slightly higher values of maximum lift-drag ratio throughout the test Mach number range than the uncambered and untwisted wing. With the moment reference centers at 0.565 wing mean aerodynamic chord, both wings were slightly unstable longitudinally at low lift coefficients. For lift coefficients greater than about 0.1, the instability became more marked. These characteristics were obtained at all Mach numbers at which tests were made. 收起