ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Tests were conducted in the 40-in. supersonic and 50-in. hypersonic tunnels of the von Karman Gas Dynamics Facility VKF to determine the maximum lift-to-drag ratios of a series of blunt leading edge, semispan delta wings having a 70-deg leading-edge sweep angle. Each wing configuration was comprised of triangular forward and tip panels and a rectangular main wing panel. Data were obtained at Mach numbers from 3 to 8 over an angel-of-attack range from -2 to 14 deg. Testing was primarily at a Reynolds number, based on the maximum wing root chord 48 in. of 14,400,000 with additional testing at Reynolds numbers of 9,600,000 and 3,400,000. Selected results are presented showing the effect of forward panel bluntness and deflection, and Mach number of the wing lift-to-drag ratios.
Prepared in cooperation with ARO, Inc., Tullahoma, Tenn. DOI: 10.21236/AD0832104