Showing papers on "Wing root published in 1968"
01 May 1968
TL;DR: In this article, the maximum lift-to-drag ratios of a series of blunt leading edge, semispan delta wings having a 70-deg leading-edge sweep angle were evaluated in the von Karman Gas Dynamics Facility (VKF).
Abstract: : 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.
2 citations
01 Apr 1968
TL;DR: In this paper, the effect of slots on the aerodynamic characteristics of a semispan 70-deg swept delta wing was evaluated at nominal Mach numbers of 6 and 10 at free-stream Reynolds numbers, based on wing root chord, and angles of attack from -2 to 14-deg.
Abstract: : Tests were conducted to determine the effect of slots on the aerodynamic characteristics of a semispan 70-deg swept delta wing. The purpose of the slots was to reduce the model viscous drag by bleeding off the windward surface boundary layer. Data were obtained at nominal Mach numbers of 6 and 10 at free-stream Reynolds numbers, based on wing root chord, of 15,200,000 and 6, 400,000 and angles of attack from -2 to 14-deg. Selected test results are presented and illustrate that the effects of the slots and Reynolds number variation were small.
1 citations