Swept-Wing Icing Research

Swept-Wing Icing and Aerodynamics Research  

Goal of Project

Improve the fidelity of experimental and computational simulation methods for swept-wing ice accretion formation and resulting aerodynamic effect.


  • Generate a database of 3D ice-accretion geometry for icing code development and validation; and for aerodynamic testing..
  • Develop a systematic understanding of the aerodynamic effect of icing on swept-wings including: Reynolds and Mach number effects, important flowfield physics and fundamental differences from 2D..
  • Determine the level of geometric fidelity required for accurate aerodynamic simulation of swept-wing icing effects.

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