Determination of the Momentum Drag within the Turbojet Engine Laboratory While Operating the J-57-8B Turbojet Engine

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Authors
Subjects
Advisors
Date of Issue
1964-09
Date
1964-09
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Limited tests were conducted at the USNPGS Astro /Aeronautical Propulsion Laboratories to determine the magnitude and variation of the momentum drag which is developed within turboject engine test chamber while operating a J-57-8B powerplant. A survey of the aerodynamic characteristics at the chamber inlet and the calculation of the momentum and energy interchange at the engine exhaust plane reveal that this restric= tive drag which penalizes the "indicated" performance of the engine is approximately 1.07» of the thrust output and varies directly with the ratio of engine thrust to secondary airflow. Further tests will be necessary to evaluate the effects of the positioning of the exhaust augmenter and the variation of the exhaust cooling water flow rate upon the secondary airflow and the resulting momentum drag. With the completion of these surveys it is anticipated that the over-all accuracy of the facility thrust measuring system will be t 0.50% throughout the thrust range of 1000 to 30,000 lbs.
Type
Technical Report
Description
Series/Report No
Department
Aeronautics
Identifiers
NPS Report Number
Technical Note No. 64T-6
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Citation
Distribution Statement
Approved for public release; distribution is unlimited.
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