Preliminary Design of a FOA Cryptosteady Energy Separator for Use in Supersonic Aircraft

Abstract

The report deals with the design of a Foa Energy Separator for use in a supersonic aircraft, the LTV F-8U Crusader. Calculations are carried out to obtain a range of exit nozzle area ratios compatible with a variety of operating conditions. The effects of variations of the peripheral rotor velocity and discharge pressures on both the hot and cold outputs are analyzed. The potential merit of using a heat exchanger in conjunction with the separator, or of using ram air rather than bleed air, is also discussed.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1972
Accession Number
AD0762579

Entities

People

  • Arshad Nawaz
  • David Sobel

Organizations

  • George Washington University

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Atmospheric Temperature
  • Back Pressure
  • Barometric Pressure
  • Coefficients
  • Equations
  • Flight Speeds
  • Flow
  • Heat Exchangers
  • Mach Number
  • Mass Flow
  • Mechanical Equipment
  • Nozzle Area Ratio
  • Separators
  • Stagnation Pressure
  • Stagnation Temperature
  • Supersonic Aircraft

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Electrical Engineering

Technology Areas

  • Hypersonics