Accession Number:

ADA230555

Title:

Numerical Analysis of an Axisymmetric Thrust Augmenting Ejector

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1990-12-01

Pagination or Media Count:

108.0

Abstract:

Use of an ejector is an effective way to increase the thrust produced by a jet. In this thesis project an axisymmetric ejector concept which had been previously explored by experiment was numerically modeled. An existing axisymmetric, internal flow code based on the explicit MacCormack method was modified to incorporate primary nozzle structure and flow injection within the flowfield. Results were compared qualitatively and quantitatively with experimental results to verify the validity of the model. Internal flow structure, difficult to obtain in experiment, is easily examined. This code may be used for parametric analysis of such ejector performance parameters as primary nozzle location, flow injection angle, diffuser area ratio, and inlet geometry to optimize future hardware configurations.

Subject Categories:

  • VSTOL

Distribution Statement:

APPROVED FOR PUBLIC RELEASE