A parallel, object-oriented framework for unsteady free-wake analysis of multi-rotor/wing systems

Joseph, Cibin; Mohan, Ranjith

doi:10.1016/j.compfluid.2020.104788

Cited by 6 publications

(2 citation statements)

References 29 publications

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“…The VLM mathematical model has seen much improvement and its application has been extended to compressible fluids [84], unsteady flow [30], and many other complex aerodynamic phenomena [29,85]. Because the simplicity and low computational cost of VLMs increase their applicability, they are still being widely used in many aviation projects instead of CFD methods, which are far more demanding [31].…”

Section: Vortex Lattice Methodsmentioning

confidence: 99%

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: Vortex Lattice Methodsmentioning

confidence: 99%

Review of vortex methods for rotor aerodynamics and wake dynamics

et al. 2022

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“…Compared with computational fluid dynamics (CFD) methods, the matrix order of potential flow methods is usually small, and the calculation efficiency is obvious, which is suitable for the steady aerodynamic forces estimation in the preliminary design. However, for unsteady flow, the wake treatment for the Lagrange method becomes complex, and the wake nodes grow rapidly when the physical time becomes longer, resulting in a significant increase of the computational cost [2], which is unacceptable for the aerodynamic design.…”

Section: Introductionmentioning

confidence: 99%

An unsteady aerodynamic model for three-dimensional wing based on augmented lifting-line method

Zhou

Guo

2022

Aeronaut. j.

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A fast numerical method for unsteady aerodynamic calculation of 3D wing is established, which is suitable for the preliminary design. Based on the lifting-line method, the aerodynamic data of the 2D aerofoil obtained by the unsteady CFD simulation is used as the model input to solve the aerodynamic force of the 3D wing. Compared with the traditional steady lifting-line method, the augmented method adopts the unsteady Kutta-Jouowski (K-J) theorem to calculate the circulation and improve the accuracy of the method through the circulation correction. The pitching motion of 3D wing at different aspect ratio and reduction frequencies are studied. The results show that the aerodynamic forces obtained by the augmented lifting-line method have good agreement with the 3D unsteady CFD calculations. Compared with 3D CFD calculation, the calculation efficiency of the improved method is increased by more than 12 times. The improved method has extensive applicability and can be used to estimate the unsteady aerodynamic forces of 3D single or multiple wing configurations.

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