HEAT TRANSFER TO COMPRESSIBLE FLUIDS FLOWING IN TUBES AT SUPERSONIC VELOCITIES.

Abstract

The design of a recovery factor apparatus for a Mach number of 2.5 has been completed. The component parts, all of which have been fabricated, are now being assembled. The design of each of these parts is briefly discussed, as each is encountered in tracing the path of the airstream through the apparatus.

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1947
Accession Number
AD0493871

Entities

People

  • K. K. Klingensmith
  • R. M. Junge

Organizations

  • Massachusetts Institute of Technology

Tags

DTIC Thesaurus Topics

  • Acoustic Properties
  • Heat Transfer
  • Mach Number
  • Motion
  • Physical Properties
  • Recovery

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow