performance of multiple configurations of a NASA one-sided ejector nozzle system. The
existing ejector nozzle system hardware was provided by NASA and was previously used for
acoustic tests. A new facility adapter duct and ejector box support brackets were designed and
fabricated by the FluiDyne Aerotest Laboratory of Aero Systems Engineering, Inc. The tests
were performed in the Channel 8 static thrust stand at ASE’s FluiDyne Aerotest Laboratory
in Plymouth, Minnesota.
Facility checkout tests were made using a standard American Society of Mechanical
Engineers (ASME) long-radius metering nozzle. These tests demonstrated facility data
accuracy at flow conditions similar to the model tests.
Channel 8 static tests included 40 ASME nozzle facility checkout tests and 24 model
tests (plus an additional 1 at no charge). The model nozzle pressure ratio varied from 1.4 to
3.0.
Test results include: thrust coefficients, thrust vector angles and location, nozzle
discharge coefficients, charging station total and static pressures, and model static pressure
distributions (in the Data Appendix).
Document ID
20200000660
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Date Acquired
February 3, 2020
Publication Date
January 1, 2020
Subject Category
Report/Patent Number
Funding Number(s)
Distribution Limits
Public
Copyright
Public Use Permitted.
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