Transonic Shock-Turbulent Boundary Layer Interactions on Spinning Axisymmetric Bodies at Zero Angle of Attack

Abstract

This report presents a detailed triple-deck theory of the transonic shock-nonseparating turbulent boundary layer interaction zones on spinning axisymmetric bodies at zero angle of attack. The theory allows a general non- equilibrium turbulent boundary layer history upstream of the interaction. We further describe the application of this theory as a local interactive module imbedded in a global composite viscous-inviscid transonic flow field prediction method which can handle two or more such interaction zones. Detailed comparisons with both experimental data and thin-layer Navier-Stokes code predictions are presented to verify the accuracy and reliability of the composite method solutions for pressure, displacement thickness, velocity profiles, shape factor and skin friction distirbutions along the body over a wide range of Mach/ Reynolds number conditions.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1983
Accession Number
ADA123389

Entities

People

  • George R. Inger

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Characteristics
  • Aircrafts
  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Mechanics
  • Pressure Distribution
  • Reliability
  • Shock Waves
  • Skin Friction
  • Three Dimensional
  • Turbulent Boundary Layer
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.