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Ice-Accretion Test Results for Three Large-Scale Swept-Wing Models in the NASA Icing Research TunnelIcing simulation tools and computational fluid dynamics codes are reaching levels of maturity such that they are being proposed by manufacturers for use in certification of aircraft for flight in icing conditions with increasingly less reliance on natural-icing flight testing and icing-wind-tunnel testing. Sufficient high-quality data to evaluate the performance of these tools is not currently available. The objective of this work was to generate a database of ice-accretion geometry that can be used for development and validation of icing simulation tools as well as for aerodynamic testing. Three large-scale swept wing models were built and tested at the NASA Glenn Icing Research Tunnel (IRT). The models represented the Inboard (20 percent semispan), Midspan (64 percent semispan) and Outboard stations (83 percent semispan) of a wing based upon a 65 percent scale version of the Common Research Model (CRM). The IRT models utilized a hybrid design that maintained the full-scale leading-edge geometry with a truncated afterbody and flap. The models were instrumented with surface pressure taps in order to acquire sufficient aerodynamic data to verify the hybrid model design capability to simulate the full-scale wing section. A series of ice-accretion tests were conducted over a range of total temperatures from -23.8 to -1.4 C with all other conditions held constant. The results showed the changing ice-accretion morphology from rime ice at the colder temperatures to highly 3-D scallop ice in the range of -11.2 to -6.3 C. Warmer temperatures generated highly 3-D ice accretion with glaze ice characteristics. The results indicated that the general scallop ice morphology was similar for all three models. Icing results were documented for limited parametric variations in angle of attack, drop size and cloud liquid-water content (LWC). The effect of velocity on ice accretion was documented for the Midspan and Outboard models for a limited number of test cases. The data suggest that there are morphological characteristics of glaze and scallop ice accretion on these swept-wing models that are dependent upon the velocity. This work has resulted in a large database of ice-accretion geometry on large-scale, swept-wing models.
Document ID
20160011353
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Broeren, Andy P. (NASA Glenn Research Center Cleveland, OH United States)
Potapczuk, Mark G. (NASA Glenn Research Center Cleveland, OH United States)
Lee, Sam (Vantage Partners, LLC Brook Park, OH, United States)
Malone, Adam M. (Boeing Co. Seattle, WA, United States)
Paul, Bernard P., Jr. (Boeing Co. Seattle, WA, United States)
Woodard, Brian S. (Illinois Univ. at Urbana-Champaign Urbana, IL, United States)
Date Acquired
September 19, 2016
Publication Date
September 1, 2016
Subject Category
Aircraft Design, Testing And Performance
Computer Programming And Software
Report/Patent Number
E-19263
AIAA Paper 2016-3733
NASA/TM-2016-219137
GRC-E-DAA-TN33383
Meeting Information
Meeting: Atmospheric and Space Environments Conference
Location: Washington, DC
Country: United States
Start Date: June 13, 2016
End Date: June 17, 2016
Funding Number(s)
CONTRACT_GRANT: NNC14TA36T
CONTRACT_GRANT: NNX12AB04A
WBS: WBS 081876.02.03.08.02.02
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Wing Aerodynamics
Wind-Tunnel Tests
Icing

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