Correlation Formulas for Laminar Shock Tube Boundary Layer

Abstract

The laminar boundary layer behind a moving shock is studied. The major objective is to obtain improved correlation formulas (valid for large W, where W is the density ratio across the shock) and to simplify the procedure for obtaining boundary‐layer parameters. Numerical solutions for shear, heat transfer, and boundary‐layer thicknesses are presented for 1 ≤ W ≤ ∞, σ = 0.67, 0.72, and 1.0 (σ is the Prandtl number) assuming constant ρμ (ρ is the density and μ, the viscosity) and an ideal gas. Correlation formulas are obtained which agree with these numerical results to within fractions of a percent. Approximate corrections for variable ρμ and real‐gas effects are then introduced. Charts and tables are presented which describe boundary layers in air (M_s ≤ 22) and argon (M_s ≤ 10).