Accession Number:

ADA164214

Title:

Two-Dimensional Confined Jet Thrust Vector Control with Flow Visualization and Variable Flow Geometry

Descriptive Note:

Master's thesis

Corporate Author:

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

Personal Author(s):

Report Date:

1985-12-01

Pagination or Media Count:

68.0

Abstract:

In this experimental investigation, the performance parameters considered were axial force, side force, and vector angle. Variables included primary pressure, exit-to-throat area ratio, and exit-to-throat axial length. With each test configuration, it was possible to define specific operating modes where the flow was oscillatory, vectoredswitchable, and vectoredunswitchable. Only one test configuration yielded a stable axial flow on which secondary injection could be used to study vectoring. Switchable flows existed only at low pressure below the range of test pressures making it impossible to study switching characteristics. Because the flows were attached over the entire range of test pressures, geometric effects were based on the study of these attached flows. Results indicate that the theoretical equations for predicting wall separation points in unconfined nozzles do not accurately predict the separation points in confined jet nozzles. Small variations in axial length, as examined in this study, had a minimal impact on nozzle performance. Primary pressure and exit-to-throat area ratio have the most significant impact on two-dimensional nozzle performance. Keywords Two dimensional flow Flow visualization Axial thrust.

Subject Categories:

  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE