Aerodynamic optimization of helicopter rear fuselage

Batrakov, A. S.; Kusyumov, A. N.; Mikhaǐlov, S. A.; Barakos, George N.

doi:10.1016/j.ast.2018.03.046

Cited by 25 publications

(6 citation statements)

References 16 publications

(22 reference statements)

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“…The full grid consists of 964 blocks. The number of cells and parameters of cells distribution were determined by the study of grid independence [3,5]. As a result, the spacing of the nearwall grid in the normal to surface direction was 1•10 −5 of the fuselage length, the cells size ratio was 1.2, and the total number of cells was 13.5•10 6 .…”

Section: Numerical Approachmentioning

confidence: 99%

Experimental and numerical simulation of the wall-pressure fluctuation on the isolated helicopter fuselage

Batrakov¹

2022

EPJ Web Conf.

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This work is devoted to wall-pressure fluctuation analysis. The object of investigation was an isolated helicopter fuselage. Investigation was carried out by experimental and numerical methods. Numerical simulation was based on RANS and DES approaches. The experiment was carried out in a lowspeed wind tunnel with an open test section. Wall-pressure fluctuation was measurement by high-frequency pressure probes ENDEVCO 8510B-2. The experimental results were compared with both DES data and results by the semi-empirical model based on the RANS simulation. It was shown that DES modelling provides a wall-pressure spectrum for low and middle-frequency parts. For simulation high-frequency part of the spectrum, the semi-empirical model is preferable.

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Section: Numerical Approachmentioning

confidence: 99%

Experimental and numerical simulation of the wall-pressure fluctuation on the isolated helicopter fuselage

Batrakov¹

2022

EPJ Web Conf.

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“…In addition to the specific blade design, optimisation of the airframe itself may result in aeroacoustic reductions. Such a study was conducted using HMB3 and focused on the design of the rear of the helicopter cabin [39]. Such optimisations involve significant computational cost, and combined with the use of the full airframe, are out of the scope of the current investigation.…”

Section: Synchrophasing Analysismentioning

confidence: 99%

A computational fluid dynamic acoustic investigation of a tiltwing eVTOL concept aircraft

Higgins

Barakos

Shahpar

et al. 2021

Aerospace Science and Technology

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“…Stalewski and Zoltak (2012) developed a parametric model of a helicopter using the PARADES software, using family section curves and guiding curves, and then redesigned the helicopter fuselage to improve its aerodynamic and geometrical properties based on the multiobjective genetic algorithm and the morphing technique. Batrakov et al (2018) presented an optimization process for the rear helicopter fuselage part using genetic algorithms and Kriging surrogate models. However, these optimization design methods based on full CFD simulations applied to a helicopter fuselage are very time-consuming.…”

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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Aerodynamic optimization of helicopter rear fuselage

Cited by 25 publications

References 16 publications

Experimental and numerical simulation of the wall-pressure fluctuation on the isolated helicopter fuselage

Experimental and numerical simulation of the wall-pressure fluctuation on the isolated helicopter fuselage

A computational fluid dynamic acoustic investigation of a tiltwing eVTOL concept aircraft

An efficient method for helicopter fuselage shape optimization

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