Numerical study of helicopter blade–vortex mechanism of interaction using large-eddy simulation

Ilie, Marcel

doi:10.1016/j.compstruc.2008.11.011

Cited by 11 publications

(4 citation statements)

References 12 publications

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“…The complexity of BVI encourages the use of numeric simulation, although the literature does report some experimental investigation (Ilie, 2009). Most numeric simulation in the literature is directed towards the aerospace industry, thus the considered Reynolds number is high (Re >10 5 ).…”

Section: Introductionmentioning

confidence: 99%

The variation in the maximum loading of a circular cylinder impacted by a 2D vortex with time of impact

Strasser

Selvam

2015

Journal of Fluids and Structures

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Direct numerical simulation is used to study the loading of a rigid, circular cylinder impacted by a 2D vortex. The vortex travels within a stream of fluid characterized by Reynolds number of 150. Vortex impact occurs at twenty-five different times within one vortex shedding cycle. Substantial variation is observed in the maximum values of the drag and lift force coefficients. This variation is due to interaction between the impinging vortex and those attached to the cylinder. As the radius of the impinging vortex is increased from one to three times the cylinder's diameter, the variation in maximum force coefficients with time of impact decreases. The variation decreases because the larger vortex alters the flow field and vortex shedding cycleprior to impacting the cylinder. For structures impacted by a vortex similar in size, significant under-prediction of the maximum loading may occur if variation in loading with vortex impact time is not considered. * where δt * is the solution time step. Selvam (1997a) provides further information concerning the implementation of the balance tensor diffusion scheme.

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Section: Introductionmentioning

confidence: 99%

The variation in the maximum loading of a circular cylinder impacted by a 2D vortex with time of impact

Strasser

Selvam

2015

Journal of Fluids and Structures

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“…The vortex equation was based on Bossel (15) . The present study is based on the recent computational investigation of BVI (17) . Figure 3 shows the instantaneous magnitude of velocities, from the final LES solution, in the near field of the aerofoil (see Fig.…”

Section: Resultsmentioning

confidence: 99%

“…For all the computations in the present analysis, a time step of 1 × 10 -6 seconds was chosen, maintaining a Courant-Friedrichs-Lewy (CFL) number smaller than unity throughout the domain and the entire simulation. Ilie (2009) performed a grid convergence analysis, using a finer grid having approximately a double number of grid points, and found identical results for the lift coefficient variation as function of time (for 0°a ngle-of-attack), indicating that the adopted gird size is adequate for LES when the aerodynamic coefficients are of concern (16) . The core size of the vortex was set equal to c/4, where c is the chord of the aerofoil and the strength of the vortex provides a 25% higher velocity than the uniform free-stream velocity.…”

Section: Nomenclaturementioning

confidence: 95%

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Parametric studies of aerofoil-vortex interaction; a numerical approach using LES

2011

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The influence of angle-of-attack and vortex-aerofoil vertical miss-distance on the aerofoil-vortex mechanism of interaction is investigated numerically using the large-eddy simulation approach. The study concerns the aerofoil-vortex interaction (AVI) phenomena encountered in the rotorcraft aerodynamics. The studies are performed for a Reynolds number of 1·3 × 106based on the chord (c= 0·2m) of the aerofoil and free-stream velocityU= 100ms−1. The studies are conducted for three different angles-of-attack (α = 0°, and α = 5°, α = 10°) and vertical miss-distances (h= 0·0m,h=−0·01,h= −0·02m) respectively. The present study shows that the magnitude of lift coefficient and flow separation, at the instant of interaction, decay with the increase of angle-of-attack and vertical miss-distance.

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Numerical simulation of aerodynamic interactions among helicopter rotor, fuselage, engine and body of revolution

Cao

Huang

2014

Sci. China Technol. Sci.

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Numerical study of helicopter blade–vortex mechanism of interaction using large-eddy simulation

Cited by 11 publications

References 12 publications

The variation in the maximum loading of a circular cylinder impacted by a 2D vortex with time of impact

The variation in the maximum loading of a circular cylinder impacted by a 2D vortex with time of impact

Parametric studies of aerofoil-vortex interaction; a numerical approach using LES

Numerical simulation of aerodynamic interactions among helicopter rotor, fuselage, engine and body of revolution

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