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Airflow calibration of a bellmouth inlet for measurement of compressor airflow in turbine-powered propulsion simulators
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Author and Affiliation:
Smith, S. C.(NASA Ames Research Center, Moffett Field, CA, United States)
Abstract: The development of turbine-powered propulsion simulators for high-speed wind tunnel models requires a bellmouth inlet which can accurately measure compressor-inlet airflow. A bellmouth inlet was instrumented with total pressure probes, static pressure probes, and thermocouples for airflow measurement. The bellmouth flowmeter against a critical venturi flowmeter was calibrated. The calibration was done at four inlet pressures ranging from 58 to 114 kPa. The bellmouth discharge coefficient varied as a function of bellmouth-throat Mach number. Over the range of Reynolds number and Mach number tested the Reynolds number was not a significant influence on the discharge coefficient. The overall accuracy of the bellmouth inlet as a flowmeter was estimated to be + or - 0.5% of the flowmeter reading.
Publication Date: Nov 01, 1985
Document ID:
19860001742
(Acquired Nov 04, 1995)
Accession Number: 86N11209
Subject Category: RESEARCH AND SUPPORT FACILITIES (AIR)
Report/Patent Number: NASA-TM-84399, REPT-85337, NAS 1.15:84399
Document Type: Technical Report
Publisher Information: United States
Contract/Grant/Task Num: RTOP 505-43-01
Financial Sponsor: NASA; United States
Organization Source: NASA Ames Research Center; Moffett Field, CA, United States
Description: 17p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AIR FLOW; COMPRESSIBLE FLOW; FLOW GEOMETRY; FLOW MEASUREMENT; INLET FLOW; MACH NUMBER; REYNOLDS NUMBER; SUPERCHARGERS; TURBOCOMPRESSORS; WIND TUNNELS
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