In-Flight icing simulation capabilities of NRC's altitude icing wind tunnel

  1. Get@NRC: In-Flight icing simulation capabilities of NRC's altitude icing wind tunnel (Opens in a new window)
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Proceedings titleAIAA 39th Aerospace Sciences Meeting and Exhibit
Series titleAIAA Paper
Conference39th AIAA Aerospace Sciences Meeting and Exhibit, Jan. 8-11, 2001, Reno, Nevada, U.S.A.
Article numberAIAA 2001-0094
Pages121; # of pages: 21
Subjectaircraft icing; icing wind tunnel; calibration
AbstractAIAA 2001 0094: An overview of the icing cloud characteristics needed to simulate in-flight icing is presented. The wider range of conditions that result from the need to test at sub-scale conditions in a wind tunnel are shown to create additional challenges for icing wind tunnels, over and above those that are encountered in nature. A detailed description of the NRC Altitude Icing Wind Tunnel (AIWT) is presented, providing background information for the discussion of recent calibrations, flow quality surveys and icing cloud investigations. The instrumentation used for these studies is described and individual measurement uncertainties are documented. The aerodynamic calibration began with measurements of total and static pressure corrections. This was followed by planar surveys of the flow quality in the test section. The calibrations were conducted at sea-level conditions. The effects on test section flow quality of spraying air through the settling chamber spray bars are documented. Spray air generally impacts the flow quality by modifying the velocity uniformity and flow angularity. Surveys of the icing cloud consisted of droplet size calibration, liquid water content (LWC) uniformity and LWC calibration. From these studies, it was found that the AIWT has acceptable LWC uniformity. New spray bars, under development at this time, should improve the icing cloud uniformity even further. Preliminary investigations of a single prototype spray bar in the AIWT show improved spray on-off transients and greater uniformity in LWC distribution. Future investigations are planned to identify the cause of reduced flow quality near the starboard wall of the test section.
Publication date
PublisherAmerican Institute of Aeronautics and Astronautics
AffiliationNational Research Council Canada; NRC Institute for Aerospace Research
Access conditionavailable
Peer reviewedYes
NRC numberAL-2001-0125
NPARC number8928744
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Record identifierac67d4f4-3dfd-4144-8b4d-3d5644bbc52d
Record created2009-04-23
Record modified2016-05-09
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