CURRENT DISTRIBUTION AND FLOW MODEL FOR LARGE RADIUS-RATIO MAST

Abstract

The non-uniform flow in a magnetic annular shock tube (MAST) with an annular spacing larger than the radius of the inner cylinder is described. Experiments were conducted in a MAST with inner and outer ra ii of 1 and 3 inches. The speed of the disturbance produced in the tube was found to depend upon the polarity of the discharge. The distribution of current in the tube was determined with probe coils; it too, depended on polarity. With the inner electrode positive the current was largely confined to a thin sheet that was strongly canted with respect to the walls, the inner edge leading. A thicker current sheet that was nearly normal to the tube walls was observed in the inverse polarity condition. A model is proposed to explain the operation with positive center electrode. The shape of the forward part of the current sheet is calculated by balancing the magnetic pressure behind the sheet with the gas pressure in front; the Newtonian approximation is used for the gas pressure. The resulting shape, which is approximately parabolic, agrees roughly with experiment. It is proposed that the dependence of the flow on polarity is associated with electron emission problems, and that in positive operation the ions carry a substantial part of the current.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1962
Accession Number
AD0274094

Entities

People

  • F. Fishman
  • H. Petschek
  • J. C. Keck

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Coordinate Systems
  • Current Density
  • Detectors
  • Dynamic Pressure
  • Electrodes
  • Electron Emission
  • Electrons
  • Emission
  • Flow
  • Government Procurement
  • Kinetic Theory
  • Magnetic Fields
  • Mass Flow
  • Mean Free Path
  • Photoexcitation
  • United States

Fields of Study

  • Physics

Readers

  • Electrical Engineering
  • Fluid Dynamics.

Technology Areas

  • Microelectronics
  • Space
  • Space - Hall-Effect Thruster