Unsteady Shock Wave - Boundary Layer Interactions FY 2000 AFOSR Entrepreneurial Research Task

Abstract

The objective of the research performed was to investigate shock - boundary layer interactions at transonic conditions in the presence of unsteady vortex flows originating upstream of the shock location. These conditions are germane to both external and internal flows: principally, flows over a geometry representative of a modern fighter wing at transonic maneuvering conditions and within transonic compressor states, respectively. Despite intentions to the contrary, these conditions were studied separately as it was determined that insufficient overlap existed for the computational tools and conditions of choice.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 2001
Accession Number
ADA412849

Entities

People

  • Gregory Addington
  • William W. Copenhaver

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Air Force Research Laboratories
  • Aircrafts
  • Boundaries
  • Boundary Layer
  • Compressors
  • Computational Fluid Dynamics
  • Generators
  • Geometry
  • Layers
  • Shock
  • Shock Waves
  • Steady State
  • Three Dimensional
  • Turbines
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design