A Numerical Solution of Supersonic and Hypersonic Viscous Flow Fields Around Thin Planar Delta Wings.

Abstract

A numerical technique was used to compute the supersonic and hypersonic, viscous flow fields around thin planar delta wings. These solutions were obtained by solving the Navier-Stokes equations subject to a conical approximation. The integration technique used was the MacCormack finite-difference scheme. Solutions were obtained for the upper-only, lower-only, and total flow fields around delta wings with supersonic leading edges.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1978
Accession Number
ADA065632

Entities

People

  • Guion S. Bluford Jr

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Computers
  • Difference Equations
  • Differential Equations
  • Fluid Dynamics
  • Fluid Flow
  • Heat Transfer
  • Partial Differential Equations
  • Pressure Distribution
  • Pressure Measurement
  • Steady State
  • Temperature Gradients
  • Turbulent Mixing
  • Viscous Flow

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics