High Altitude Aerodynamic Tests with Simulated Heat-Shield Outgassing

Abstract

This report presents the results from the High Altitude Side Force Test conducted in the NSWC Hypervelocity Wind Tunnel at Mach 14. Test objectives were to provide static force and moment data as well as pressure and heat transfer distributions on typical reentry configurations with asymmetric boundary layer outgassing. The results include normal force and moment, yaw force and moment, surface pressures and surface heat transfer rate on both 7 degree and 9 degree blunt cone models. These models incorporated a circumferentially asymmetric outgassing distribution.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1982
Accession Number
ADA132078

Entities

People

  • Charles Fiscina
  • Eric R. Hedlund
  • Mark M. Roberts
  • Robert L. Voisinet

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Diameters
  • Dynamic Pressure
  • Equations
  • Flow Rate
  • Fluid Flow
  • Heat Transfer
  • High Altitude
  • Internal Pressure
  • Measurement
  • Mechanical Properties
  • Molecular Dynamics
  • Pressure Distribution
  • Pressure Gages
  • Pressure Measurement
  • Pressure Transducers
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

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