论文信息 - Preliminary study of effects of Reynolds number and boundary-layer transition location on shock-induced separation - 字舞流文

Preliminary study of effects of Reynolds number and boundary-layer transition location on shock-induced separation

Transonic wind tunnel studies on airfoil to determine effects of Reynolds number and boundary layer transition location on shock induced separated flow

J. A. Blackwell

[1] D. L. Loving. Wind-tunnel-flight correlation of shock-induced separated flow , 1966 .

[2] Albert L. Braslow,et al. Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5 , 1958 .

[3] E Truckenbrodt. A method of quadrature for calculation of the laminar and turbulent boundary layer in case of plane and rotationally symmetrical flow , 1955 .

[4] S. C. Sommer,et al. Free-flight measurements of turbulent-boundary-layer skin friction in the presence of severe aerodynamic heating at Mach numbers from 2.8 to 7.0 , 1955 .

[5] Don D Davis,et al. Analytical study of blockage- and lift-interference corrections for slotted tunnels obtained by the substitution of an equivalent homogeneous boundary for the discrete slots , 1954 .