An Investigation of the Flowfleld for an Integrated Airframe/Propulsion System

Abstract

This report results from a contract tasking USAFA/DFAN as follows: The contractor will modify an existing wind tunnel model of a hypersonic vehicle to incorporate devices that permit control of the onset of boundary layer transition. He will conduct comprehensive wind tunnel tests to determine the ct on the forebody flowfield of fixing the transition location.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1997
Accession Number
ADA332525

Entities

People

  • Alois F. Kreins

Organizations

  • United States Air Force Academy

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Heat Transfer Coefficients
  • Laser Induced Fluorescence
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Three Dimensional
  • Two Dimensional
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow