NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsIce-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 ID20160011353Acquisition SourceGlenn Research CenterDocument TypeTechnical Memorandum (TM)AuthorsBroeren, 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 AcquiredSeptember 19, 2016Publication DateSeptember 1, 2016Subject CategoryAircraft Design, Testing And PerformanceComputer Programming And SoftwareReport/Patent NumberE-19263AIAA Paper 2016-3733NASA/TM-2016-219137GRC-E-DAA-TN33383Meeting InformationMeeting: Atmospheric and Space Environments ConferenceLocation: Washington, DCCountry: United StatesStart Date: June 13, 2016End Date: June 17, 2016Funding Number(s)CONTRACT_GRANT: NNC14TA36TCONTRACT_GRANT: NNX12AB04AWBS: WBS 081876.02.03.08.02.02Distribution LimitsPublicCopyrightPublic Use Permitted.KeywordsWing AerodynamicsWind-Tunnel TestsIcingAvailable DownloadsNameType20160011353.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsIDRelationTitle20170002540See AlsoIce Accretion Test Results for Three Large-Scale Swept-Wing Models in the NASA Icing Research Tunnel20170000227See AlsoIce-Accretion Test Results for Three Large-Scale Swept-Wing Models in the NASA Icing Research Tunnelvisibility_offNo Preview Available
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