Quantitative effects of Prandtl number and viscosity-temperature index on the compressible laminar boundary layer with pressure gradient
The transformed, non-dimensional boundary layer equations defining the velocity and enthalpy are solved by a series method. Numerical solutions for three types of main stream flow (accelerated, uniform, and retarded) are given for Prandtl number, σ, of 1.0 and 0.725 and viscosity-temperature index, ω, of 1.0 and 0.76. The solutions allow estimates of the effects of σ and ω to be made. They also form standards for testing approximate solutions.
- Crocco, L.: Laminar Boundary Layer in Gases. Monografie Scientifieche Di Aeronautica, No. 3, Dec. 1946 (R. A. E. Library Translation No. 218).Google Scholar
- Canetti, G. S.: A Generalization of the Problem of the Compressible Laminar Boundary Layer with Solutions for an Idealized Fluid. University of London Thesis, June, 1950.Google Scholar
- Howarth, L.: Steady Flow in the Boundary Layer Near the Surface of a Cylinder in a Stream. A. R. C. R & M. 1632, July, 1934.Google Scholar
- Young, A. D.: Skin Friction in the Laminar Boundary Layer in Compressible Flow. The Aero. Quart., Vol. 1. Part II, August, 1949.Google Scholar
- Gadà, G. E.: Some Aspects of Laminar Boundary Layer Separation in Compressible Flow with no Heat Transfer to the Wall. The Aero. Quart., Vol. IV, Part II, February, 1953.Google Scholar
- Laurmann, J. A.: Stability of the Compressible “Boundary Layer with an External Pressure Gradient. Col. of Aero., Cranfield, Rep. No. 48, September, 1951.Google Scholar