Computation of Shock Layers about Ablated, Blunt-Nosed Bodies.

Abstract

A technique is described to calculate steady, inviscid, supersonic flows past blunt-nosed vehicles affected by ablation. New computational grids are created by conformal mapping. Stretching of coordinates for further application to viscous flows is demonstrated. The technique does not apply to flows with imbedded shocks. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1977
Accession Number
ADA044619

Entities

People

  • Gino Moretti

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Aerodynamics
  • Blunt Bodies
  • Bodies
  • Bow Shock
  • Computational Fluid Dynamics
  • Equations
  • Equations Of Motion
  • Flow
  • Fluid Dynamics
  • Fluid Mechanics
  • Gas Dynamics
  • Hydrodynamics
  • Military Research
  • New York
  • Steady Flow
  • Steady State
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight