Accession Number:

AD0478344

Title:

CORRELATION FORMULAS FOR LAMINAR SHOCK TUBE BOUNDARY LAYER.

Descriptive Note:

Technical documentary rept.,

Corporate Author:

AEROSPACE CORP EL SEGUNDO CALIF

Personal Author(s):

• Mirels,H.

Report Date:

1965-12-01

Pagination or Media Count:

38.0

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 infinity, Prandtl Number 0.67, 0.72 and 1.0 assuming constant rho mu rho density and mu 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 rho mu and real gas effects are then introduced. Charts and tables are presented which describe boundary layers in air Ms or 22 and argon Ms or 10. Author

Descriptors:

• (*LAMINAR BOUNDARY LAYER
• *SHOCK TUBES)
• SHOCK WAVES
• DENSITY
• SHEAR STRESSES
• HEAT TRANSFER
• THICKNESS
• VISCOSITY
• CORRECTIONS
• HYPERSONIC FLOW
• HYPERSONIC CHARACTERISTICS
• SURFACE TEMPERATURE
• AIR
• ARGON
• NUMERICAL ANALYSIS

Subject Categories:

• Test Facilities, Equipment and Methods
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE