University of Hertfordshire

Numerical and experimental investigations into protection net icing at the helicopter engine inlet

Research output: Contribution to journalArticlepeer-review

  • Jincheng Tang
  • Yongqi Xie
  • Jianqin Zhu
  • Xianwei Wang
  • Siyuan Liu
  • Jianzu Yu
  • Hongwei Wu
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Original languageEnglish
JournalAircraft Engineering and Aerospace Technology
Publication statusAccepted/In press - 29 Mar 2021


The ice shapes of the protection net at different times are firstly simulated by a 2D icing calculation, then the porous media parameters are calculated based on the 2D ice shapes. Afterwards, a three-dimensional (3D) flow fields of the engine inlet with the iced net are simulated using the porous media model instead of the real protection net. The transient pressure losses of the iced protection net are calculated and tested through an icing wind tunnel test rig under different icing conditions. Overall the numerical results and experimental data shows a good agreement. The effects of several control parameters such as liquid water contents (LWC), water droplet diameters, and airflow velocities on the pressure loss of the protection net during the icing process are analyzed in a systematic manner. The results indicate that the pressure loss increases with the increase of the LWC at the same icing time. The same trend occurs when the water droplet diameter and the airflow velocity increase.

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