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

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.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1972
Accession Number
AD0743003

Entities

People

  • John C. Adams Jr.

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Computational Fluid Dynamics
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Heat Transfer
  • Hypersonic Wind Tunnels
  • Measurement
  • Pressure Distribution
  • Thermal Conductivity
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers