Numerical and Experimental Study on Aerodynamic Approximation Methods for Inclined Honeycomb Grid Fins

Longfei Li, Guiyu Zhou, Huan Li, Lei Luo, Pengcheng Cui, Xiaojun Wu and Hongyin Jia ()
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Longfei Li: Computational Aerodynamic Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
Guiyu Zhou: Computational Aerodynamic Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
Huan Li: Computational Aerodynamic Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
Lei Luo: Computational Aerodynamic Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
Pengcheng Cui: Computational Aerodynamic Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
Xiaojun Wu: Computational Aerodynamic Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
Hongyin Jia: Computational Aerodynamic Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Energies, 2025, vol. 18, issue 18, 1-19

Abstract: Wind tunnel experiment serves as a primary method for characterizing grid fin aerodynamics, yet a fundamental conflict arises between facility size constraints and the structural vulnerability of excessively thinned grid fins from aggressive scaling, which might prevent viable experiments from being conducted. This study addresses this limitation by proposing two aerodynamic approximation methods, namely the unconstrained cell chord ratio method and the unconstrained external frame dimensions method, which generate aerodynamically equivalent configurations by strategically reducing the number of cells within the external frame to increase structural thickness. Through combined computational fluid dynamics (CFD) simulations and wind tunnel experiments analyzing full-scale isolated grid fins, full-scale launch vehicles equipped with grid fins, and their 1:25 scaled counterparts, both methods demonstrably outperform the published supersonic linearization approximation method. Critically, once the cell number is not excessively reduced, the unconstrained frame method maintains identical variation trends in aerodynamic forces, moments, and rudder control effectiveness compared to the baseline configuration, with maximum deviations constrained within 3% across tested conditions. This precision validates the exceptional suitability of the method for aerodynamic approximation of scale-down grid-fin-equipped launch vehicles in wind tunnel experiments, resolving the critical trade-off between test feasibility and structural strength.

Keywords: grid fin; launch vehicle; aerodynamic approximation method; computational fluid dynamics; wind tunnel experiment (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2025
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