INVESTIGATION OF MINIMUM DRAG AND MAXIMUM LIFT-DRAG RATIOS OF SEVERAL WING-BODY COMBINATIONS INCLUDING A CAMBERED TRIANGULAR WING AT LOW REYNOLDS NUMBERS AND AT SUPERSONIC SPEEDS

摘要

Wing-body combinations incorporating several wing plan forms indicated to be of interest from a theoretical analysis were tested at Mach numbers of 1.62, 1.93, and 2.4l in the Langley 9-inch supersonic tunnel. One triangular, one arrow, and two diamond plan forms were tested. The triangular and arrow plan forms were tested with various amounts of camber, which was designed to yield an approximately uniform pressure distribution. Tests of the arrow and triangular wings showed that cambering the surface was an effective way to reduce the leading-edge laminar-separation effects which were present at the low test Reynolds numbers. For the models tested, the laminar separation at the leading edges prevented the possibility of attaining the theoretically predicted leading-edge thrust. The principal conclusions resulting from both the tests and comparison with other available experiments and theory are as follows。