A Method for Calculating the Interaction of a Bow Shock of a Re-Entry Vehicle and a Blast Wave

Abstract

A general technique for computing the transient flow field in the nose region of a blunt body traveling at hypersonic speeds after being intercepted head-on by a shock wave is presented. The method is not limited to the assumption that the density, pressure and velocities are constant in the interaction region which has been the assumption in previous investigations of this problem. The technique can be applied to compute the flow in the entire interaction region, but is discussed here for computing the low near the axis of symmetry.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1964
Accession Number
AD0612733

Entities

People

  • Thomas D. Taylor

Organizations

  • Picatinny Arsenal

Tags

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Mechanics and Fluid Dynamics.
  • Geodesy

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow