Performance of Turbo Jet Engines Under the Influence of Supersonic Flight Disturbances(Leistungsverhalten von turbostrahltriebwerken unter dem einfluss von hyperschallflug-typischen eintrittsstroerungen)

Abstract

This engineering dissertation investigates the impact of typical supersonic intake disturbances on the performance of a turbojet engine. Wind tunnel experiments are used to calculate the effects of Mach numbers and Reynold's numbers on a model-sized subsonic diffuser. A simulator is used to find ways to improve the performance of a turbo jet engine under supersonic conditions.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2000
Accession Number
ADA427650

Entities

People

  • Norbert R. Schmid

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Diffusers
  • Engineering
  • Fluid Dynamics
  • Gas Turbines
  • Jet Engines
  • Propulsion Systems
  • Simulations
  • Simulators
  • Subsonic Diffusers
  • Test Facilities
  • Turbines
  • Turbofan Engines
  • Turbojet Engines
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computer Programming and Software Development.
  • Snow Cover Descriptors for Reptiles and Their Illustrations.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow