Chocking of a Subsonic Induction Tunnel by the Flow from an Induction Nozzle

Abstract

A decrease in Mach number with increase in induction-jet pressure has been shown to occur experimentally in one type of induct ion tunnel at induction-jet pressures in excess of the lowest value required to attain the highest subsonic Mach number. This performance characteristic was analytically demonstrated to be associated with choking of the induced flow by the flow from the induction nozzle. The analysis provides a means of predicting the occurrence of induction choking so that it can be adequately considered in design. Use of an auxiliary induction nozzle operating as a choker is suggested as a means of controlling the speed of a tunnel.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1952
Accession Number
ADA377187

Entities

People

  • W. F. Lindsey

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Barometric Pressure
  • Boundary Layer
  • Diffusers
  • Equations
  • Experimental Data
  • Flow
  • Jet Flow
  • Mach Number
  • Mass
  • Mass Flow
  • Specific Heat
  • Stagnation Pressure
  • Static Pressure
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Cellular and Molecular Pathways of Apoptosis.
  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.