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Total Temperature Measurements in Icing Cloud Flows Using a Rearward Facing ProbeThis paper reports on temperature and humidity measurements from a series of ice-crystal icing tunnel experiments conducted in June 2018 at the Propulsion Systems Laboratory at the NASA Glenn Research Center. The tests were fundamental in nature and were aimed at investigating the icing processes on a two-dimensional NACA0012 airfoil subjected to artificially generated icing clouds. Prior to the tests on the airfoil, a suite of instruments, including total temperature and humidity probes, were used to characterize the thermodynamic flow and icing cloud conditions of the facility. Two different total temperature probes were used in these tests which included a custom designed rearward facing probe and a commercial self-heating total temperature probe. The rearward facing probe, the main total temperature probe, was designed to reduce and mitigate the contaminating effects of icing and ingestion of ice crystals and water droplets at the probe's inlet. The probe also serves as an air-sample inlet for a light absorption based humidity measurement. The paper includes a section which discusses total temperature and humidity measurement considerations, and another section which provides an analysis of the main probe's performance characteristics. A computational fluid dynamic model of the flow around the probe was also conducted to gain insight into the trajectory of the flow entering the probe inlet. The experiments included a series of tests in which the relative humidity of the facility flow was swept through with increasingly larger values. The data showed that the rearward facing probe can reasonably capture the flow's total temperature and humidity under mild to moderate icing conditions but produces anomalous results under more intense icing conditions. The experimental data was also compared to an in-house developed thermodynamic model which takes into account the interaction of the main flow with the icing cloud. Comparison to the thermodynamic model showed that the rearward facing probe measured the predicted trends.
Document ID
20190027071
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Agui, Juan H.
(NASA Glenn Research Center Cleveland, OH, United States)
Struk, Peter M.
(NASA Glenn Research Center Cleveland, OH, United States)
Bartkus, Tadas P.
(Ohio Aerospace Inst. Brook Park, OH, United States)
Date Acquired
July 9, 2019
Publication Date
June 17, 2019
Subject Category
Engineering (General)
Report/Patent Number
GRC-E-DAA-TN67171
Report Number: GRC-E-DAA-TN67171
Meeting Information
Meeting: International Conference on Icing of Aircraft, Engines, and Structures
Location: Minneapolis, MN
Country: United States
Start Date: June 17, 2019
End Date: June 21, 2019
Sponsors: Society of Automotive Engineers, Inc.
Funding Number(s)
WBS: 081876.02.03.08.01.04
CONTRACT_GRANT: NNC13BA10B
Distribution Limits
Public
Copyright
Public Use Permitted.
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