On the Solution to the Problem of the Flow around a V-Shaped Wing with an Intense Shock Wave on the Leading Edge,

Abstract

A report is made on the effect of initial and boundary conditions on the numerical solution to the problem of the flow around a V-shaped wing with supersonic leading edges.

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1974
Accession Number
AD0775108

Entities

People

  • V. I. Lapygin

Organizations

  • National Air and Space Intelligence Center

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Leading Edges
  • Shock
  • Shock Waves
  • Waves

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Operations Research

Technology Areas

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