RAREFIED HYPERSONIC FLOW OVER A SPHERE.

Abstract

The flow over a sphere at large hypersonic Mach numbers and low Reynolds numbers was computed by using the Navier-Stokes equations as simplified by Probstein and Kemp. A similarity solution, valid about the stagnation streamline, is used. Both the adiabatic and cold wall cases are treated. Solutions, in particular the shock structure, the inviscid compression zone, and the stagnation point boundary layer were obtained at a Mach number of 10 and Reynolds numbers of 10,000 1,000, and 100 based on the sphere radius, free stream velocity, and adiabatic stagnation values of density and viscosity. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1961
Accession Number
AD0682314

Entities

People

  • E. S. Levinsky
  • Hideo Yoshihara

Organizations

  • General Dynamics

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Hypersonic Flow
  • Mach Number
  • Navier Stokes Equations
  • Reynolds Number
  • Stagnation Point

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow