Passive Nosetip Technology (PANT) Program. Volume 19. Hydrometeor/Shock Layer Interaction Study

Abstract

Hypersonic vehicles during reentry may experience extensive damage due to encounters with condensed phase H2O(hydrometeors) in the form of either ice particles or liquid droplets. These encounters, which can lead to augmented heating rates and mechanical erosion, must traverse the shocked gas enveloping the reentry vehicle prior to impacting the surface. The shock layer can, depending on flight conditions, vehicle configuration, and particle size, have a marked influence on the hydrometeors traversing the region between the shock wave and the body surface. Hence, an understanding of hydrometeor/shock layer interaction is required in order to predict impact conditions from specified vehicle configuration and free stream conditions. This report documents the results of an investigation directed at surveying a portion of the phenomenology associated with the interaction between water droplets and strong shock waves.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1975
Accession Number
ADA026615

Entities

People

  • B. Laub
  • M. R. Wool
  • N. A. Jaffe
  • W. E. Nicolet

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Energy
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Heat Transfer Coefficients
  • Mach Number
  • Mass Transfer
  • Particle Size
  • Pressure Distribution
  • Stagnation Point
  • Steady State
  • Surface Temperature
  • Surface Tension
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Atmospheric Remote Sensing.
  • Combustion Dynamics and Shock Wave Physics.

Technology Areas

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