Numerical Modeling of Helicopter Main Rotor Behavior near a Small-Scale Helideck by the Vortex Method

Aparinov, A. A.; Kritskii, B. S.; Setukha, A. V.

doi:10.3103/s1068799817040043

Cited by 5 publications

(4 citation statements)

References 5 publications

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“…Recently, Morency [25] applied the NL UVLM with alpha coupling to compute the heat transfer coefficient, but the hover simulations close to the ground were more challenging. The vortex panel method has also been used to simulate a rotor near a helideck [50], but the coefficient of thrust showed oscillations of the order of 20%. Difficulties with a strictly connected wake of panels motivated the rotorcraft aerodynamic community to consider alternative wake representation, such as the VPM.…”

Section: Introductionmentioning

confidence: 99%

A Hybrid Non-Linear Unsteady Vortex Lattice-Vortex Particle Method for Rotor Blades Aerodynamic Simulations

Proulx-Cabana

Nguyen

Prothin

et al. 2022

Fluids

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This study presents a hybrid non-linear unsteady vortex lattice method-vortex particle method (NL UVLM-VPM) to investigate the aerodynamics of rotor blades hovering in and out of ground effect. The method is of interest for the fast aerodynamic prediction of helicopter and smaller rotor blades. UVLM models the vorticity along the rotor blades and near field wakes with panels that are then converted into their equivalent vortex particle representations. The standard Vreman subgrid scale model is incorporated in the context of a large eddy simulation for mesh-free VPM to stabilize the wake development via particle strength exchange (PSE). The computation of the pairwise interactions in the VPM are accelerated using the fast-multipole method. Non-linear UVLM is achieved with a low computational cost viscous-inviscid alpha coupling algorithm through a stripwise 2D Reynolds-averaged Navier–Stokes (RANS) or empirical database. The aerodynamics of the scaled S76 rotor blades in and out of ground effect from the hover prediction workshop is investigated with the proposed algorithm. The results are validated with experimental data and various high-fidelity codes.

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Section: Introductionmentioning

confidence: 99%

A Hybrid Non-Linear Unsteady Vortex Lattice-Vortex Particle Method for Rotor Blades Aerodynamic Simulations

Proulx-Cabana

Nguyen

Prothin

et al. 2022

Fluids

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“…This allows accurate modeling of the field of induced velocities around the rotor. Vortex models are used to solve problems of rotor aerodynamics in ground effects in such works as [16]- [18]. The work by Griffiths et al (2002) [16] is based on the vortex model FWM (Free Wake Model) and it considers a combination of two rotors in ground effect.…”

Section: Introductionmentioning

confidence: 99%

“…The work by Zhao & He (2014) [17] is based on the VPM (Vortex Particle Method) method and considers various issues of main and tail rotors' aerodynamics, covering the mutual aerodynamic interference in ground effect. The work by Aparinov et al (2017) [18] has also used a vortex model and it is focused on the study of helicopter rotor aerodynamics near a limited ground surface (ship's helideck). An important advantage of vortex models is their relatively low requirement for computing resources.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of the Main Rotor Wake Structures and Induced Velocity Fields at the Tail Rotor Location When Flying Near the Ground

Ignatkin

Makeev

Shomov

et al. 2021

IREASE

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The distance from the rotor's hub to the ground surface in the range of H = 6-16 m and the values of free stream (flight) velocity in the range of V = 0-15 m/s are considered. The results of the visualization for both rotor wake shapes and streamlines are obtained. The influence of the ground proximity on the rotor wake shape, including the formation of "supervortex" and "ground vortex" structures are analyzed. The induced velocity fields of the main rotor in the area of the tail rotor location for various azimuth positions relative to the main rotor axis are studied. The conclusion is made about the significant influence of the ground effect on the rotor wake structure and induced velocities field, including the area of the tail rotor location. Particularly, at slip flight with speed V = 10 m/s, when the distance to the ground surface H increases from 6 to 12 m, the value of the average induced velocity at the tail rotor plane is growing up to four times. The obtained data have allowed taking into account such effects of aerodynamic interference in the simplified mathematical model of the research flight simulator of JSC Helicopters Mil and Kamov.

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“…This problem is solved rather accurately for 2D flows being simulated using the above mentioned viscous vortex domains method [5]. For 3D case there are modifications of vortex methods which are suitable for vortex wakes simulation behind thin surfaces and bodies with preliminary specified separation lines, where the vortex wake is simulated as thin vortex sheet in the flow, which is attached to the given separation line, so the range of application of such approach is restricted to flows with rather simple structure of the vortex wake [6]. When the structure of the vortex wake is more complicated, it can not be considered as set of thin vortex sheets and more general approaches are required.…”

Section: Introductionmentioning

confidence: 99%

On the Algorithms for Vortex Element Evolution Modelling in 3D Fully Lagrangian Vortex Loops Method

Marchevsky¹,

Shcheglov²,

Dergachev³

2020

Topical Problems of Fluid Mechanics 2020

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Some implementation details of fully Lagrangian vortex loops method algorithm are presented. The vortex loops method can be applied to various engineering applications, where it is required to simulate the flow around the body of arbitrary shape and to estimate hydrodynamic loads. The original approach is implemented that permits to solve boundary integral equation with rather high accuracy at coarse and non-uniform body surface triangulation. Vorticity distribution in the flow is simulated by closed vortex loops. The presented algorithm allows to simulate movement of the vortex loops, which simulate vorticity distribution in the flow, their stretching, reconnection, etc. Note, that the viscosity influence is taken into account only through vorticity generation on the body surface.

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Numerical Modeling of Helicopter Main Rotor Behavior near a Small-Scale Helideck by the Vortex Method

Cited by 5 publications

References 5 publications

A Hybrid Non-Linear Unsteady Vortex Lattice-Vortex Particle Method for Rotor Blades Aerodynamic Simulations

A Hybrid Non-Linear Unsteady Vortex Lattice-Vortex Particle Method for Rotor Blades Aerodynamic Simulations

Numerical Study of the Main Rotor Wake Structures and Induced Velocity Fields at the Tail Rotor Location When Flying Near the Ground

On the Algorithms for Vortex Element Evolution Modelling in 3D Fully Lagrangian Vortex Loops Method

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