VISCOUS, HYPERSONIC FLOW AROUND A BLUNT BODY

Abstract

A simplified form of the Navier-Stokes equations was used to describe the flow in the shock layer of a blunt body. The equations are solved near the axis of the body by using the method of series truncation. The main method of solution is a finite difference method, which in principle allows one to handle axisymmetric bodies of arbitrary shape. The body shape is assumed to be given and the bow shock shape is determined step by step.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1968
Accession Number
AD0669578

Entities

People

  • I. Fluegge-lotz
  • John E. Kaiser

Organizations

  • Stanford University

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Value Problems
  • Computational Fluid Dynamics
  • Computational Science
  • Difference Equations
  • Differential Equations
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Geometry
  • Navier Stokes Equations
  • Partial Differential Equations
  • Pressure Distribution
  • Three Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow