Shock Interaction Surface Pressures for Hemispherical and Conical Bodies

Abstract

Transient pressures, induced by wind-tunnel simulated head-on blast wave interactions, have been measured on a hemisphere and on cones of 9-, 15- and 30-degree semivertex angles. Blast wave Mach numbers of 1.6 to 2.2, 2.2 to 5.85 and 2.7 to 4.4 were simulated at the free-stream Mach numbers of 3.1, 5.1 and 7, respectively. Measured pressure-time histories for the hemisphere were compared and found in agreement with histories predicted by McNamara's FLAME code. Peak overpressures for the cones were tested for agreement with values predicted by a simple theoretical method in which an assumption is made that the blast wave forms a Mach stem moving along the surface at a velocity whose axial component equals the velocity of the main blast wave. The effects of angle of attack and of nose blunting were also investigated with the nine-degree cone at a free-stream Mach number of 5.1.

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Document Details

Document Type
Technical Report
Publication Date
Feb 16, 1971
Accession Number
AD0883047

Entities

People

  • Frank P. Baltakis

Organizations

  • Naval Ordnance Laboratory

Tags

DTIC Thesaurus Topics

  • Angle Of Incidence
  • Blast Waves
  • Bodies
  • Boundaries
  • Boundary Layer
  • Conical Bodies
  • Experimental Data
  • Flow
  • Free Stream
  • Geometry
  • Mach Number
  • Measurement
  • Munitions
  • Ordnance Laboratories
  • Photographs
  • Pressure Distribution
  • Pressure Measurement
  • Pressure Transducers
  • Shock Waves
  • Stagnation Point

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Dynamics.