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Test and numerical prediction of ice accretions on civil aircraft wing.[J]. Journal of Aerospace Power, 2017, 32(1): 22-26. doi: 10.13224/j.cnki.jasp.2017.01.004
Citation: Test and numerical prediction of ice accretions on civil aircraft wing.[J]. Journal of Aerospace Power, 2017, 32(1): 22-26. doi: 10.13224/j.cnki.jasp.2017.01.004
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Test and numerical prediction of ice accretions on civil aircraft wing.

doi: 10.13224/j.cnki.jasp.2017.01.004
  • Received Date: 2015-04-16
  • Publish Date: 2017-01-28
    Abstract
  • The ice accretion test results on civil aircraft wing in Italy IWT (icing wind tunnel) were described. The numerical prediction of ice shapes was conducted based on the Lagrange method and Messinger model according to the icing wind tunnel test states. The icing shape test and numerical prediction results were compared and analyzed. A conclusion can be drawn that the numerical results and test data of the rime ice are consistent, while there is difference between those of the glaze ice. The possible reasons can be listed as follows: (1) the airflow variation during the glaze ice accretion strengthens the unsteady effect on icing prediction; (2) the icing thermal model adopted has some limitation for glaze ice prediction; (3) the icing wind tunnel work states and the test model roughness are sensitive to glaze ice accretion.

     

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