THE BLUNT-LEADING-EDGE PROBLEM IN HYPERSONIC FLOW

Abstract

Study was made of the hypersonic flow over a flat plate with a blunt nose. The analysis is based on the flow model in which the flow field behind the shock wave may be divided into two regions: (1) the inviscid-hypersonic-flow region and (2) the entropy layer, across which the pressure undergoes no appreciable change. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1961
Accession Number
AD0272083

Entities

People

  • Hakuro Oguchi

Organizations

  • Cornell University

Tags

DTIC Thesaurus Topics

  • Flow
  • Flow Fields
  • Hypersonic Flow
  • Leading Edges
  • Shock
  • Shock Waves
  • Waves

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers