AN ARC PLASMA CHANNEL FOR TESTING OF REENTRY BOUNDARY LAYER INSTRUMENTATION.

Abstract

This report describes a reentry boundary layer instrumentation test facility composed of a rectangular channel to which a laminar plasma flow is supplied from a subsonic arc jet. Use of a channel flow permits boundary layer development simulating the peaked temperature and number density profiles in the boundary layers of conical hypersonic reentry vehicles. Detailed diagnostic experiments leading to average and profile determinations of temperature, electorn number density, and velocity are described. Use of a sliding interchangeable test section makes possible utilization of small diameter uncooled probes for determination of flow profiles. (Author)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1966
Accession Number
AD0807210

Entities

People

  • Donald J. Spencer
  • Keith E. Starner

Organizations

  • The Aerospace Corporation

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Buildings And Structures
  • Channel Flow
  • Diameters
  • Flow
  • Hypersonic Reentry Vehicles
  • Instrumentation
  • Layers
  • Measuring Instruments
  • Reentry Vehicles
  • Test Facilities
  • Vehicles

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow