A Parallel Unstructured Overset Mesh Technique for Unsteady Flow Simulations

Jung, Mun Seung; Kwon, Oh Joon

doi:10.1007/978-3-540-92779-2_48

Cited by 5 publications

(8 citation statements)

References 7 publications

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“…An unstructured overset mesh technique (Jung and Kwon, 2007) was adopted to manage the relative motion between the main rotor, fuselage, and tail rotor. In this overset mesh scheme, the mesh topology was composed of multiple independent mesh blocks.…”

Section: Methodsmentioning

confidence: 99%

“…For this purpose, a three-dimensional flow solver (Jung et al, 2007) based on unstructured meshes was used. An overset mesh technique was adopted to effectively manage the relative motion of those components.…”

Section: Kwonetal Numerical Investigation Of Aerodynamic Interferenmentioning

confidence: 99%

“…UH-60A flight tests were conducted in 1993-1994 for the NASA/Army UH-60A Airloads Program (Kufeld et al, 1994). The flight conditions cover level flights and transient maneuvers, and the measured data included aerodynamic pressures, structural loads, control positions, and rotor forces and moments.…”

Section: Uh-60a Configurationmentioning

confidence: 99%

“…In previous studies, lifting line/free-wake methods coupled with a potential theory were used (Lorber and Egolf, 1990;Mavris et al, 1989;Wachspress et al, 2003). These methods are…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Numerical Investigation of Aerodynamic Interference in Complete Helicopter Configurations

Lee¹,

Yu²,

Kwon³

et al. 2011

International Journal of Aeronautical and Space Sciences

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Unsteady flow simulations of complete helicopter configurations were conducted, and the flow fields and the aerodynamic interferences between the main rotor, fuselage, and tail rotor were investigated. For these simulations, a three-dimensional flow solver based on unstructured meshes was used, coupled with an overset mesh technique to handle relative motion among those components. To validate the flow solver, calculations were made for a UH-60A complete helicopter configuration at high-speed and low-speed forward flight conditions, and the unsteady airloads on the main rotor blade were compared to available flight test data and other calculated results. The results showed that the fuselage changed the rotor inflow distribution in the main rotor blade airloads. Such unsteady vibratory airloads were produced on the fuselage, which were nearly in-phase with the blade passage over the fuselage. The flow solver was then applied to the simulation of a generic complete helicopter configuration at various flight conditions, and the results were compared with those of the CAMRAD-II comprehensive analysis code. It was found that the main rotor blades strongly interact with a pair of disk-vortices at the outer edge of the rotor disk plane, which leads to high pulse airloads on the blade, and these airloads behave differently depending on the specific flight condition.

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Section: Methodsmentioning

confidence: 99%

Section: Kwonetal Numerical Investigation Of Aerodynamic Interferenmentioning

confidence: 99%

Section: Uh-60a Configurationmentioning

confidence: 99%

“…In previous studies, lifting line/free-wake methods coupled with a potential theory were used (Lorber and Egolf, 1990;Mavris et al, 1989;Wachspress et al, 2003). These methods are…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical Investigation of Aerodynamic Interference in Complete Helicopter Configurations

Lee¹,

Yu²,

Kwon³

et al. 2011

International Journal of Aeronautical and Space Sciences

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“…To handle multiple bodies in relative motion effectively, an overset mesh scheme was adopted [13]. For the overset mesh method, a search procedure is needed for the identification of donor cells that contain the verticies from the opposite overlapping mesh block.…”

Section: Unstructured Overset Mesh Techniquementioning

confidence: 99%

Numerical Simulation of Rotor-Fuselage Aerodynamic Interaction Using an Unstructured Overset Mesh Technique

Lee¹,

Jung²,

Kwon³

et al. 2010

International Journal of Aeronautical and Space Sciences

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Numerical simulation of unsteady flows around helicopters was conducted to investigate the aerodynamic interaction of main rotor and other components such as fuselage and tail rotor. For this purpose, a three-dimensional inviscid flow solver has been developed based on unstructured meshes. An overset mesh technique was used to describe the relative motion between the main rotor, and other components. As the application of the present method, calculations were made for the rotorfuselage aerodynamic interaction of the ROBIN (ROtor Body INteraction) configuration and for a complete UH-60 helicopter configuration consisted of main rotor, fuselage, and tail rotor. Comparison of the computational results was made with measured time-averaged and instantaneous fuselage surface pressure distributions for the ROBIN configuration and thrust distribution and available experimental data for the UH-60 configuration. It is demonstrated that the present method is efficient and robust for the simulation of complete rotorcraft configurations.

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Evaluation of the overset grid method for control studies of wave energy converters in OpenFOAM numerical wave tanks

Windt

Davidson

Chandar

et al. 2019

J. Ocean Eng. Mar. Energy

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Computational fluid dynamics (CFD) based numerical wave tanks are valuable tools for the development and evaluation of energy maximising control systems for wave energy converters (WECs). However, the exaggerated body motion amplitude, which can be induced by the energy maximising control system, challenges the commonly applied mesh morphing method in CFD, due to the resulting mesh distortion and subsequent numerical instability. A more advanced mesh motion method is the overset grid method, which can inherently handle large amplitude body motions and has recently become freely available in the open source CFD software OpenFOAM. The overset grid method can, therefore, potentially eliminate the mesh distortion problem, hindering the simulation of WECs under controlled conditions. To evaluate the capability of the overset grid method for control studies of WECs in an OpenFOAM numerical wave tank, this paper presents a detailed comparison of the overset grid and mesh morphing methods, considering five test cases of increasing complexity. The test cases range from a static equilibrium test to the modelling of a controlled WEC, and good agreement is demonstrated between the two mesh motion methods, except for the case of the controlled WEC, when the device motion becomes

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A Parallel Unstructured Overset Mesh Technique for Unsteady Flow Simulations

Cited by 5 publications

References 7 publications

Numerical Investigation of Aerodynamic Interference in Complete Helicopter Configurations

Numerical Investigation of Aerodynamic Interference in Complete Helicopter Configurations

Numerical Simulation of Rotor-Fuselage Aerodynamic Interaction Using an Unstructured Overset Mesh Technique

Evaluation of the overset grid method for control studies of wave energy converters in OpenFOAM numerical wave tanks

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