A VPM/CFD Coupling Methodology to Study Rotor/Ship Aerodynamic Interaction

Rajmohan, Nischint; He, Chengjian

doi:10.2514/6.2016-1915

Cited by 14 publications

(6 citation statements)

References 6 publications

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“…Advanced Rotorcraft Technology, Inc. developed a coupled vortex particle method (VPM) and CFD analysis model in which VPM and CFD are employed to resolve the wake vorticity dynamics and to compute the near-body flow solution, respectively [36,37]. VPM is used to solve the dynamics of wakes generated by rotors, wings, and other rotorcraft components, convect the wake vorticity under the combined influence of the freestream, and account for self-induced wake velocities and flow field perturbations caused by bodies like the fuselage.…”

Section: Hybrid Vortex Methodsmentioning

confidence: 99%

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Review of vortex methods for rotor aerodynamics and wake dynamics

et al. 2022

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Electric vertical take-off and landing (eVTOL) aircraft with multiple lifting rotors or prop-rotors have received significant attention in recent years due to their great potential for next-generation urban air mobility (UAM). Numerical models have been developed and validated as predictive tools to analyze rotor aerodynamics and wake dynamics. Among various numerical approaches, the vortex method is one of the most suitable because it can provide accurate solutions with an affordable computational cost and can represent vorticity fields downstream without numerical dissipation error. This paper presents a brief review of the progress of vortex methods, along with their principles, advantages, and shortcomings. Applications of the vortex methods for modeling the rotor aerodynamics and wake dynamics are also described. However, the vortex methods suffer from the problem that it cannot deal with the nonlinear aerodynamic characteristics associated with the viscous effects and the flow behaviors in the post-stall regime. To overcome the intrinsic drawbacks of the vortex methods, recent progress in a numerical method proposed by the authors is introduced, and model validation against experimental data is discussed in detail. The validation works show that nonlinear vortex lattice method (NVLM) coupled with vortex particle method (VPM) can predict the unsteady aerodynamic forces and complex evolution of the rotor wake.

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Section: Hybrid Vortex Methodsmentioning

confidence: 99%

“…Leishman and Bhagwat [39] provided more detailed information on this matter. Abedi et al [160] suggested the VLM with the free-wake method to (36…”

Section: Time-marching Free-wake Methodsmentioning

confidence: 99%

Review of vortex methods for rotor aerodynamics and wake dynamics

et al. 2022

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“…In recent years, first-principle-based rotorcraft aerodynamics methods (i.e. Navier-Stokes-based CFD airloads solvers) have been interfaced with FLIGHTLAB to offer a coupled CFD/CSD solution (8) .…”

Section: Flightlab – Air Vehicle Modelling and Simulation Softwarementioning

confidence: 99%

“…For detailed design and analysis, the flow field is modelled using VPM to capture the interactional aerodynamics of all vorticity producing elements (6-11) . Interfacing to CFD codes provides high-fidelity modelling of the airloads (8) . For structural loads analysis, finite element modelling of the rotor is used and a modal representation of the fuselage, obtained from a NASTRAN model, is used to couple the modal fuselage response with a full finite element NASTRAN model of the fuselage.…”

Section: Validationmentioning

confidence: 99%

Validation of the FLIGHTLAB virtual engineering toolset

Val

2018

Aeronaut. j.

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As simulation has become an integral part of the overall life-cycle support of aircraft, the need for effective Virtual Engineering (VE) tools to support these activities has increased. FLIGHTLAB is a state-of-the-art, aircraft modelling and simulation software tool, that has been designed to address this need and is widely used in rotorcraft design, analysis, test and evaluation, and full-flight simulation applications. This VE tool supports the development and analysis of both fixed and rotary wing aircraft with an extensive library of modelling components which have been successfully used and validated in numerous, real-world applications. These components provide comprehensive modelling of aerodynamic, structural, control and propulsion disciplines. Analyses include performance, dynamic response, stability and control, airloads, and structural loads. Graphical User Interfaces and an interactive scripting language provide user-friendly operation. This paper describes the capabilities and validation activities that have been undertaken to support the development of the commercial VE toolset FLIGHTLAB over the last 20 years and discusses future rotorcraft challenges that could be addressed by enhancements to current generation VE tools.

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“…In this work, Gaussian smoothing kernel, with order , was used. Gaussian smoothing regularisation function is a common choice for regularised vortex particles, as in Refs (58,59,71,72,73).…”

Section: Introductionmentioning

confidence: 99%

Propeller influence on the aeroelastic stability of High Altitude Long Endurance aircraft

Teixeira

Cesnik

2020

Aeronaut. j.

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This work investigates the propeller’s influence on the stability of High Altitude Long Endurance aircraft, incorporating all resultant loads at the propeller hub, propeller slipstream, and gyroscopic loads. Such effects are usually neglected in the aeroelastic simulation of HALE aircraft. For that goal, a previously developed framework, which couples a geometrically nonlinear structural solver with an Unsteady Vortex Lattice method (uVLM) for lifting surfaces and a Viscous Vortex Particle (VVP) method for propeller slipstream, was employed to generate time-data series. Also, a method, based on a combination of Proper Orthogonal Decomposition and system identification, to extract dynamic information (frequencies, damping, and modes) of the aircraft from a time-series signal is proposed and successfully tested for a purely structural case, for which reference data is available. The method is then applied to investigate the stability of aeroelastic cases. The results demonstrate that the presence of propellers can influence the aeroelastic stability of a Very Flexible Aircraft.

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A VPM/CFD Coupling Methodology to Study Rotor/Ship Aerodynamic Interaction

Cited by 14 publications

References 6 publications

Review of vortex methods for rotor aerodynamics and wake dynamics

Review of vortex methods for rotor aerodynamics and wake dynamics

Validation of the FLIGHTLAB virtual engineering toolset

Propeller influence on the aeroelastic stability of High Altitude Long Endurance aircraft

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