Accession Number:

ADA048445

Title:

Estimates of Turbulent Boundary Layer Behind a Shock Wave Moving with Uniform Velocity.

Descriptive Note:

Interim rept.,

Corporate Author:

AEROSPACE CORP EL SEGUNDO CALIF IVAN A GETTING LABS

Personal Author(s):

Report Date:

1977-12-08

Pagination or Media Count:

35.0

Abstract:

A theory, previously presented by the author, concerning turbulent boundary-layer development behind a shock moving with uniform speed is briefly reviewed. Numerical results for boundary-layer properties are presented for shock propagation in air at Mach numbers in the range 1.01 or M sub S or 20. The heat transfer results are in good agreement with the shock tube wall heat transfer measurements of Hartunian et al., which were made in the range 3 or M sub S 8. Approximate analytical expressions for turbulent boundary-layer properties are deduced, and estimates of the wall temperature variation with distance behind the shock assumed small are given. Effects of blowing wall ablation are also estimated. The need for experimental data to confirm large Mach number and blowing effects predictions is also noted. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE