Simulation of a complete helicopter: A CFD approach to the study of interference effects

Biava, Massimo; Vigevano, Luigi

doi:10.1016/j.ast.2011.08.006

Cited by 17 publications

(9 citation statements)

References 10 publications

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“…Academia also plays a leading role in rotorcraft CFD code development. In-house codes HMB from the University of Glasgow [5] and ROSITA from Politecnico di Milano [6] are both finite-volume solvers and utilize structured Chimera multi-block grids to account for the blade motion. Each of the codes have been part of large-scale collaborations for the assessment of their predictive capabilities such as the GOAHEAD project [7].…”

Section: Introductionmentioning

confidence: 99%

Development and preliminary assessment of the open-source CFD toolkit SU2 for rotorcraft flows

Morelli

Bellosta

Guardone

2021

Journal of Computational and Applied Mathematics

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Computational aerodynamic analyses of rotorcraft main rotor blades are performed in both hover and forward flight. The open-source SU2 code is used for rotor performance prediction. The core of the code is the set of RANS equations, which are solved for determining the flow. In hover, both steady-state and time-accurate modelling techniques of varying complexity are used and assessed. Simulation specific parameters which have a significant influence on the solution are also addressed. In forward flight, the code is developed to include the main rotor blade kinematics which is a prerequisite for modelling a trimmed rotor. Two databases are used for the validation of the rotor performance prediction. The renowned Caradonna-Tung experimental tests of a model rotor are used to evaluate the pressure distribution along the blade during hover. The extensive aerodynamic and aeroacoustic data survey of the AH-1G Cobra helicopter is used to assess the pressure distribution at different advancing and retreating azimuth angles during forward flight. The prediction capabilities of the solver in terms of rotor performance are demonstrated and are overall in good agreement with the measured data.

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Section: Introductionmentioning

confidence: 99%

Development and preliminary assessment of the open-source CFD toolkit SU2 for rotorcraft flows

Morelli

Bellosta

Guardone

2021

Journal of Computational and Applied Mathematics

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“…This has led to closer understanding of the interaction mechanisms and advancing the prediction capability of complete helicopter configurations. The studies can be categorized as purely experimental or experimental and theoretical work [4][5][6][7][8][9][10][11][12], simple analytical or numerical work that uses simplified aerodynamic and structural models [13][14][15][16][17][18][19][20][21][22][23], and numerically more involved work that directly solves computational fluid dynamics (CFD) equations like Euler or Navier-Stokes (in form of Reynolds-averaged Navier-Stokes = RANS) for the rotorcraft flow field [24][25][26][27][28][29][30][31][32][33][34]. Even though the direct usage of CFD is viable and sometimes desired in predicting the complicated interaction behavior accurately, it is still computationally expensive and prohibitive especially for cases within the preliminary design stage of a rotorcraft.…”

Section: Introduction and Objectivesmentioning

confidence: 99%

Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: influence of side-slip angle

Wall

Yin

2016

CEAS Aeronaut J

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A semi-empirical and physics-based analytical formulation of the induced velocities generated by the fuselage shell of the Bo105 wind tunnel model in the volume around the rotor is derived from velocity data computed by a panel code. The reduced-order analytical model is several orders of magnitude faster than the panel code and thus is predestinated for use in comprehensive rotor codes. Angle of attacks investigated include vertical descent, shallow descent, level flight and climb to vertical ascent. Side-slip angles range from forward to quartering flight. The analytical induced velocity model can be directly used to account for the inflow at the blade elements and also allows for analytical or numerical integration of rotor wake convection to compute the associated displacements of rotor blade tip vortices travelling downstream within this velocity field. This model will be used to replace a fully panelized fuselage (and thus significantly reduce the computational effort) throughout a simulation with an aeromechanics code to account for the influence of the fuselage (e.g., in a design stage). The usage within an aerodynamics code (e.g., a panel code) reduces the panelization to the rotor blades only, leaving the computation of the fuselage-induced velocities to the model. The focus of this paper is the analytical evaluation of fuselagerotor interference in side-slip angles on rotor trim controls, using blade element momentum theory. The results are compared to the influence of thrust-induced inflow gradients on rotor trim.

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“…Most of the times, engineers are looking for small changes in geometry and structure to improve an already good design. Past and recent studies (for isolated fuselages and full helicopter models) show that a significant contributor to the total drag of the helicopter fuselage is suction at its rear due to aft-facing surfaces used for ramps and rear-access [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15]. This is the reason for streamlined helicopter fuselage shapes.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic optimization of helicopter rear fuselage

Batrakov

Kusyumov

Mikhaǐlov

et al. 2018

Aerospace Science and Technology

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An optimization process for the rear helicopter fuselage part is presented using Genetic Algorithms and Kriging surrogate models. Shape parameterization is carried out with the super ellipse technique employed for the well-known ROBIN fuselage. The simulations were based on the RANS equations solved using the HMB CFD code. It is shown that a decrease of fuselage drag around 2.5% is possible without compromising the structure and the functionality of the design. Combined with an optimization of the helicopter skids, benefits of up to 4.6% were possible. The demonstrated method can be applied to fuselages of any shape during the initial design phase.

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Simulation of a complete helicopter: A CFD approach to the study of interference effects

Cited by 17 publications

References 10 publications

Development and preliminary assessment of the open-source CFD toolkit SU2 for rotorcraft flows

Development and preliminary assessment of the open-source CFD toolkit SU2 for rotorcraft flows

Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: influence of side-slip angle

Aerodynamic optimization of helicopter rear fuselage

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