Accession Number:

AD0769648

Title:

Shock Wave - Boundary Layer Interaction in Hypersonic Flow.

Descriptive Note:

Final scientific rept. Jan 70-Mar 73,

Corporate Author:

CALSPAN CORP BUFFALO N Y

Personal Author(s):

• Holden,Michael S.

Report Date:

1973-10-01

Pagination or Media Count:

81.0

Abstract:

A study is presented of attached and separated turbulent viscous interaction regions resulting from shock wave-boundary layer interaction in hypersonic flow. The direct measurements of surface shear indicated that turbulent boundary layer separation occurred well before an inflection point was observed in the surface pressure distribution through the interaction region. It was found that the incipient separation conditions for both shock- and wedge-induced interaction regions can be correlated in terms of the local Mach number and the properties of the turbulent boundary layer ahead of the interaction. The length of the separated regions induced both by externally generated shocks and on compression surfaces was found to increase with increasing Reynolds number and wall-to-free stream stagnation temperature and decreasing Mach number of the free stream. Correlations for the plateau pressure and the heat transfer rate at reattachment and in the plateau region are presented. The fluctuating pressure measurements indicated that turbulent viscous interaction regions in separated flow are highly unsteady, and that this unsteadiness is reflected in the observed motion of the separation and reattachment points. Modified author abstract

Descriptors:

• (*Hypersonic flight
• Interactions)
• Boundary layer
• Shock waves
• Inviscid flow
• Flow separation
• Turbulent flow

Subject Categories:

• Aerodynamics
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE