GLTRS--Glenn
TITLE AND SUBTITLE:
Unsteady Ejector Performance: An Experimental Investigation Using a Resonance Tube Driver

AUTHOR(S):
Jack Wilson and Daniel E. Paxson

REPORT DATE:
July 2002

FUNDING NUMBERS:
WU-708-48-13-00

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
John H. Glenn Research Center at Lewis Field
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-13239

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-2002-211474
AIAA-2002-3632

SUPPLEMENTARY NOTES:
Prepared for the 38th Joint Propulsion Conference and Exhibit cosponsored by AIAA, ASME, SAE, and ASEE, Indianapolis, Indiana, July 7-10, 2002. Jack Wilson, QSS Group, Inc., Cleveland, Ohio, and Daniel E. Paxson, NASA Glenn Research Center. Responsible person, Jack Wilson, organization code 5810, 216-977-1204.

ABSTRACT:
A statistically designed experiment to characterize thrust augmentation for unsteady ejectors has been conducted at the NASA Glenn Research Center. The variable parameters included ejector diameter, length, and nose radius. The pulsed jet driving the ejectors was produced by a shrouded resonance (or Hartmann-Sprenger) tube. In contrast to steady ejectors, an optimum ejector diameter was found, which coincided with the diameter of the vortex ring created at the pulsed jet exit. Measurements of ejector exit velocity using a hot-wire permitted evaluation of the mass augmentation ratio, which was found to correlate to thrust augmentation following a formula derived for steady ejectors.

SUBJECT TERMS:
Ejectors; Thrust augmentation

NUMBER OF PAGES:
20

PDF AVAILABLE FROM URL:
2002/TM-2002-211474.pdf
( 439 KB )
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