Approximate Turbulent Boundary-layer Development in Plane Compressible Flow Along Thermally Insulated Surfaces with Application to Supersonic-tunnel Contour Correction
Auteur : Maurice Tucker
Date de publication : 1950
Éditeur : National Advisory Committee for Aeronautics
Nombre de pages : 78
Résumé du livre
With the tabulations presented, the approximate development of a turbulent boundary layer in two-dimensional and in radial shock-free flow under arbitrary pressure-gradient variation can be obtained through routine arithmetic computations for Mach number range from 0.100 to 10. An experimental check of the method at a nominal Mach number of 2 is presented.