CFD – a key element of helicopter activities at the IAG

Wagner, Siegfried; Keßler, Manuel; Altmikus, Andree; Pomin, Hubert; Ostertag, J.; Eckart, Bernd; Fischer, Andreas; Landmann, Björn

doi:10.1016/j.ast.2003.10.005

Cited by 1 publication

(1 citation statement)

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“…But the accuracy of the panel method is limited by these same conditions. The CFD method based on RANS has made progress in the accuracy of its computations (Wagner et al , 2003). The CFD method has been used to calculate the flow field of a transport helicopter fuselage (Vogel et al , 2011) and to predict the drag of the isolated fuselage and of different components of the ANSAT helicopter, which have been verified by wind tunnel tests (Kusyumov et al , 2012).…”

Section: Introductionmentioning

confidence: 99%

An efficient method for helicopter fuselage shape optimization

Zhu

Shi

2023

AEAT

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Purpose This paper aims to develop a new method of fuselage drag optimization that can obtain results faster than the conventional methods based on full computational fluid dynamics (CFD) calculations and can be used to improve the efficiency of preliminary design. Design/methodology/approach An efficient method for helicopter fuselage shape optimization based on surrogate-based optimization is presented. Two numerical simulation methods are applied in different stages of optimization according to their relative advantages. The fast panel method is used to calculate the sample data to save calculation time for a large number of sample points. The initial solution is obtained by combining the Kriging surrogate model and the multi-island genetic algorithm. Then, the accuracy of the solution is determined by using the infill criteria based on CFD corrections. A parametric model of the fuselage is established by several characteristic sections and guiding curves. Findings It is demonstrated that this method can greatly reduce the calculation time while ensuring a high accuracy in the XH-59A helicopter example. The drag coefficient of the optimized fuselage is reduced by 13.3%. Because of the use of different calculation methods for samples, this novel method reduces the total calculation time by almost fourfold compared with full CFD calculations. Originality/value To the best of the authors’ knowledge, this is the first study to provide a novel method of fuselage drag optimization by combining different numerical simulation methods. Some suggestions on fuselage shape optimization are given for the XH-59A example.

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Section: Introductionmentioning

confidence: 99%