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Ice Accretion Test Results for Three Large-Scale Swept-Wing Models in the NASA Icing Research Tunnel

NASA NTRS · Presentation · 20170002540 · Published 2019-07-12 · Glenn Research Center · 6 authors

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Abstract and citation only, verbatim from NASA NTRS; full text lives there. All credit to the authors and Glenn Research Center.

Abstract

The design and certification of modern transport airplanes for flight in icing conditions increasing relies on three-dimensional numerical simulation tools for ice accretion prediction. There is currently no publically available, high-quality, ice accretion database upon which to evaluate the performance of icing simulation tools for large-scale swept wings that are representative of modern commercial transport airplanes. The purpose of this presentation is to present the results of a series of icing wind tunnel test campaigns whose aim was to provide an ice accretion database for large-scale, swept wings.

Authors

  • Broeren, Andy NASA Glenn Research Center
  • Potapczuk, Mark NASA Glenn Research Center
  • Lee, Sam Vantage Partners, LLC
  • Malone, Adam Boeing Commercial Airplane Co.
  • Paul, Ben Boeing Commercial Airplane Co.
  • Woodard, Brian Illinois Univ. at Urbana-Champaign

Keywords

  • Wind-Tunnel Tests
  • Wing Aerodynamics
  • Icing

Citation

Broeren, Andy , Potapczuk, Mark , Lee, Sam , et al. (2019). Ice Accretion Test Results for Three Large-Scale Swept-Wing Models in the NASA Icing Research Tunnel. Glenn Research Center. NASA NTRS ID 20170002540. https://ntrs.nasa.gov/citations/20170002540 ↗