Laminar Boundary Layer Behind a Strong Shock Moving into Air

摘要: The laminar wall boundary layer behind a strong shock advancing into stationary air has been determined. Numerical results have obtained for Mach numbers up to 14 using real gas values density and viscosity assuming Prandtl Lewis of 0.72 1, respectively. numerical shear heat transfer agree, within 4 percent, with previously presented approximate analytical expression these quantities. A slight modification this in agreement the data 2.5 percent. Analytical expressions boundary-layer thickness displacement thickness, correct percent present data, also obtained.