Further Consideration on the Design of a Foa Cryptosteady Energy Separator for Use in Supersonic Aircraft

Abstract

It is shown in the report that a fixed geometry Foa Energy Separator can satisfy the cooling requirements of the F-8U aircraft without an external heat exchanger or staged configuration. A possible solution involves a hot to cold side nozzle area ratio of 0.283, dual pre-rotation at one half the rotor speed, and regenerative precooling at the Energy Separator entrance.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1973
Accession Number
AD0762032

Entities

People

  • Arshad Nawaz
  • David Sobel

Organizations

  • George Washington University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Altitude
  • Barometric Pressure
  • Creep
  • Energy
  • Equations
  • Flow
  • Geometry
  • Heat Energy
  • Heat Exchangers
  • Mach Number
  • Mass Flow
  • Nozzle Area Ratio
  • Separators
  • Stagnation Pressure
  • Stagnation Temperature
  • Supersonic Aircraft

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Control Systems Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow