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Design and analysis of simulated ice for a civil aircraft airfoil
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DOI：10.1177/07316844261435073.png)
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Abstract
En 中文
Natural icing flight tests are costly and risky, necessitating reliable simulated ice models for airworthiness certification. This study presents a novel approach utilizing a 3D-printed sandwich composite (UV-curable resin core with GFRP skins) to replicate critical ice shapes for dry air flight testing. Computational fluid dynamics (CFD) simulations quantified the aerodynamic degradation, revealing that leading-edge ice accretion reduces the maximum lift coefficient by 24.1% at 0.4 Ma and advances the stall angle by 2 degrees due to premature flow separation. A finite element model incorporating cohesive zone elements and the Tsai-Wu failure criterion was developed to assess the structural integrity of the simulated ice. The results indicate that the simulated ice exhibits negligible deformation (less than 0.2% of the chord length) while maintaining sufficient safety margins under aerodynamic loading, which is accurately mapped to structural nodes using the inverse-distance weighting interpolation method. This study provides a feasible implementation scheme for dry air flight test with simulated ice, offering high safety reliability while fully complying with airworthiness requirements.
Keywords:
Simulated ice
sandwich composite structure
CFD
finite element analysis
airworthiness certification
structural integrity
Journal
J
IF:
2.2
Papers:
117
Citations:
6.7K
Organization
Cited Papers