A.D. Young

The effects of viscosity on the aerodynamic characteristics of wings and bodies at supersonic speeds can be assessed if we can calculate (a) the development of the boundary layers in the laminar and turbulent states, (b) the interaction of the boundary layers and main stream away from the neighborhood of shock waves, (c) the effects of shock wave-boundary layer interaction. Comprehensive methods are developed and discussed for dealing with problems (a) and (b), problem (c) is discussed in the light of existing experimental data but more systematic data are required before quantitative prediction of shock wave boundary layer interaction effects in any particular case can be confidently made. Fortunately, for many practical cases of interest the latter effects are small. The detailed results of calculations made on the lines described in this paper for a wide range of aerofoil thickness, body fineness ratio, Reynolds number, Mach number and transition position will be given in a subsequent report.

WGL-Tagung, Göttingen, 1953

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

Jahrbuch der Wissenschaftlichen Gesellschaft für Luftfahrt 1953; S.66-76; Braunschweig : Vieweg; 1954

NA

Bestellbar

1954