Accession Number:

AD0743003

Title:

Analysis of the Three-Dimensional Compressible Turbulent Boundary Layer on a Sharp Cone at Incidence in Supersonic and Hypersonic Flow

Descriptive Note:

Final rept. Jul 71-Feb 72,

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

• Adams, Jr, John C.

Report Date:

1972-06-01

Pagination or Media Count:

94.0

Abstract:

An analytical approach toward numerical calculation of the three- dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three- dimensional turbulent boundary-layer equations in conjunction with a three- dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure velocity and temperature profiles, the surface streamline direction obtained via an oil-flow technique and surface heat-transfer rate.

Descriptors:

• *REENTRY VEHICLES
• *TURBULENT BOUNDARY LAYER
• AERODYNAMIC CHARACTERISTICS
• ANGLE OF ATTACK
• CONICAL BODIES
• EXPERIMENTAL DATA
• FLOW FIELDS
• MATHEMATICAL MODELS
• NUMERICAL ANALYSIS
• THERMAL PROPERTIES
• THREE DIMENSIONAL FLOW
• WALLS
• WIND TUNNEL MODELS

Subject Categories:

• Guided Missile Reentry Vehicles
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE