Development of a Prediction Method for Transonic Shock Induced Separated Flow.

Abstract

In the present study it has been demonstrated that a finite difference technique for viscous-inviscid interaction, previously developed and demonstrated by the author for subsonic turbulent separated flows, is applicable to the problem of transonic shock induced separated flow. Converged solutions have been obtained and favorable comparisons with experimental data show that this method is capable of resolving the detailed features of this strongly interacting flow. These interaction calculations are aided by the use of a new shear layer coordinate system which is aligned with an estimated position of the shear layer in the large separated region. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1981
Accession Number
ADA104566

Entities

People

  • J. E. Carter

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Coordinate Systems
  • Equations
  • Experimental Data
  • Flow Visualization
  • Fluid Dynamics
  • Inviscid Flow
  • Navier Stokes Equations
  • Pressure Distribution
  • Pressure Gradients
  • Shock Waves
  • Skin Friction
  • Turbulent Flow
  • Turbulent Mixing
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Fluid Dynamics.