It was found that the maximum lift to drag ratio of a flat delta wing at moderate supersonic and hypersonic speeds can be increased appreciably by letting a small amount of air pass through narrow gaps located at proper places on the wing. The increase in (L/D)max obtained from such a wing experiment varies from 5% to 17% at different speeds. Six gap configurations were tested at four different free stream Mach numbers, M = 4, 4.5, 5 and 8. Reynold's number was kept constant at Re/in = 300,000 and 700,000. Both the lift and drag of the wing were reduced due to the presence of gaps. Since the decrease in drag is greater than that of lift, L/D is thus increased. The reduction in lift is due to the loss of momentum and the increase of pressure in the induced separation region on the leeward side of the wing; the reduction in drag is due to the decrease in skin-friction caused by gap effects. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Research on Hypersonic Flow of Blunt delta Wings. Part II. Gap Effects of a Blunt Slab delta Wing at Moderate Supersonic and Hypersonic Speeds


    Contributors:
    B. Mazelsky (author) / C. C. Chao (author)

    Publication date :

    1968


    Size :

    86 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Flow over a Delta Wing and Blunt Body Combination at Hypersonic Speeds

    Singh, A. | British Library Online Contents | 1994


    Flow over a Delta Wing and Blunt Body Combination at Hypersonic Speeds

    Singh, A. / International Council of Aeronautical Sciences | British Library Conference Proceedings | 1994




    Numerical study of hypersonic leeward flow over a blunt nosed delta wing

    Mallett, E.R. / Pullin, D.I. / Macrossan, M.N. | Tema Archive | 1995