Ice-accretion test results for three large-scale swept-wing models in the NASA icing research tunnel

Andy P. Broeren, Mark G. Potapczuk, Sam Lee, Adam M. Malone, Bernard P. Paul, Brian S. Woodard

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Icing 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% semispan), Midspan (64% semispan) and Outboard stations (83% semispan) of a wing based upon a 65% 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 °C 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 °C 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.

Original languageEnglish (US)
Title of host publication8th AIAA Atmospheric and Space Environments Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104336
DOIs
StatePublished - 2016
Event8th AIAA Atmospheric and Space Environments Conference, 2016 - Washington, United States
Duration: Jun 13 2016Jun 17 2016

Publication series

Name8th AIAA Atmospheric and Space Environments Conference

Conference

Conference8th AIAA Atmospheric and Space Environments Conference, 2016
CountryUnited States
CityWashington
Period6/13/166/17/16

ASJC Scopus subject areas

  • Space and Planetary Science
  • Atmospheric Science

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    Broeren, A. P., Potapczuk, M. G., Lee, S., Malone, A. M., Paul, B. P., & Woodard, B. S. (2016). Ice-accretion test results for three large-scale swept-wing models in the NASA icing research tunnel. In 8th AIAA Atmospheric and Space Environments Conference (8th AIAA Atmospheric and Space Environments Conference). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2016-3733