Application of a Shock-Turbulent Boundary Layer Interaction Theory in Transonic Flow Field Analysis.

Abstract

This paper describes the application of non-asymptotic triple-deck theory of transonic shock-turbulent boundary layer interaction as a local modular element in the global calculation of supercritical airfoil flow fields. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 18, 1980
Accession Number
ADA103244

Entities

People

  • G. R. Inger

Organizations

  • University of Colorado Boulder

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Airfoils
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Engineering
  • Flow
  • Flow Fields
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Reynolds Number
  • Skin Friction
  • Supercritical Airfoils
  • Transonic Flow
  • Turbulent Boundary Layer
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.