Finite Difference Solutions to the Interacting Supersonic Turbulent Boundary Layer Equations, Including Separation Effects.

Abstract

A numerical algorithm is presented for the solution of the supersonic interacting turbulent boundary layer equations including separation effects. A representative eddy viscosity model is used to describe turbulent stress. Mach 3 cold wall flow up a compression ramp at (Re sub infinity) = 100,000 is used to demonstrate the fundamental technique. The numerical algorithm developed is a relaxation technique taylored after the implicit alternating direction method employed for boundary value partial differential equation systems. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1974
Accession Number
AD0778785

Entities

People

  • A. Polak
  • M. J. Werle
  • S. D. Bertke

Organizations

  • University of Cincinnati

Tags

DTIC Thesaurus Topics

  • Algorithms
  • Boundaries
  • Boundary Layer
  • Compression
  • Differential Equations
  • Equations
  • Layers
  • Mathematics
  • Partial Differential Equations
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics