The Three-Dimensional Shock and Pressure (3DSAP) Approximate Flow Field Technique. Volume 1. Engineering Analysis

Abstract

An approximate flow field technique is developed for the prediction of inviscid aerodynamic characteristics of re-entry vehicles with asymmetric nose geometries at angle of attack and/or sideslip. The subsonic flow region on the nose is approximated using a correlation for surface pressures and iterating on the shock position to satisfy mass continuity. The axisymmetric frustum is computed using the exact three-dimensional inviscid equations, explicitly treating crossflow effects.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1977
Accession Number
ADB029574

Entities

People

  • Darryl W. Hall

Organizations

  • General Electric

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Computational Fluid Dynamics
  • Computational Science
  • Coordinate Systems
  • Equations
  • Equations Of Motion
  • Equations Of State
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Mach Number
  • Pressure Distribution
  • Test And Evaluation
  • Thermodynamic Properties
  • Thermodynamics
  • Three Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.