Experimental Measurements of Hypersonic Instabilities over Ogive Cylinders at Mach 6

Abstract

Hypersonic boundary layer transition experiments were performed in the Air Force Research Lab (AFRL) Mach 6 Ludwieg tube over a meter long ogive-cylinder model with interchangeable nose tip angles and bluntnesses. Measurements of instabilities were captured via focused laser differential interferometry (FLDI), surface mounted pressure sensors, and high speed Schlieren imagery at nominal unit Reynolds numbers ranging from 4.0*10^6/m to 1.4*10^7/m. This study attempts to isolate the effects of increasing tip angle and spherical bluntness on instabilities measured downstream over the cylindrical body of the model.

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Document Details

Document Type
Technical Report
Publication Date
Mar 26, 2020
Accession Number
AD1101505

Entities

People

  • Jonathan L. Hill

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Boundary Layer
  • Boundary Layer Control
  • Computational Fluid Dynamics
  • Computational Science
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Frequency Bands
  • Geometry
  • Hydrodynamics
  • Hypersonic Vehicles
  • Lasers
  • Measurement
  • Physics Laboratories
  • Pressure Distribution
  • Pressure Measurement
  • Research Facilities
  • Turbulent Flow
  • Turbulent Mixing
  • Two Dimensional
  • Viscous Flow
  • Wave Propagation
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Directed Energy
  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow