Panel/full-span free-wake coupled method for unsteady aerodynamics of helicopter rotor blade

Tan, Jianfeng; Wang, Haowen

doi:10.1016/j.cja.2013.04.050

Cited by 12 publications

(10 citation statements)

References 22 publications

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“…The non-linear inflows states can be analyzed by Finite State Inflow method (Gennaretti et al, 2015), which can be used to model flight dynamics and aeroelastic analysis of a rotorcraft. Panel methods, which describe surfaces as velocity potentials, allow unsteady analyses (Tan and Wang, 2013). However, not accounting for important phenomena, the aforementioned methods cannot be treated as a source of high confidence results in propeller analysis.…”

Section: Propeller Aerodynamic Modelsmentioning

confidence: 99%

Aerodynamic design and optimization of propellers for multirotor

Klimczyk

2021

AEAT

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Purpose This paper aims to present a methodology of designing a custom propeller for specified needs. The example of propeller design for large unmanned air vehicle (UAV) is considered. Design/methodology/approach Starting from low fidelity Blade Element (BE) methods, the design is obtained using evolutionary algorithm-driven process. Realistic constraints are used, including minimum thickness required for stiffness, as well as manufacturing ones – including leading and trailing edge limits. Hence, the interactions between propellers in hex-rotor configuration, and their influence on structural integrity of the UAV are investigated. Unsteady Reynolds-Averaged Navier–Stokes (URANS) are used to obtain loading on the propeller blades in hover. Optimization of the propeller by designing a problem-specific airfoil using surrogate modeling-driven optimization process is performed. Findings The methodology described in the current paper proved to deliver an efficient blade. The optimization approach allowed to further improve the blade efficiency, with power consumption at hover reduced by around 7%. Practical implications The methodology can be generalized to any blade design problem. Depending on the requirements and constraints the result will be different. Originality/value Current work deals with the relatively new class of design problems, where very specific requirements are put on the propellers. Depending on these requirements, the optimum blade geometry may vary significantly.

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Section: Propeller Aerodynamic Modelsmentioning

confidence: 99%

Aerodynamic design and optimization of propellers for multirotor

Klimczyk

2021

AEAT

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“…The turbulent flows are usually computed through solving Reynolds-averaged Navier-Stokes equations (RANS). The generation numerical modelling consists of defining the appropriate geometry, grid generation and solve for necessary boundary conditions [19]. Since the amphibious structure is complex and capturing the turbulent flow characteristics is crucial for…”

Section: Numerical Approach or Modellingmentioning

confidence: 99%

“…In addition, comparative evaluation of k-ε, k-ω and shear stress transport (SST) k-ω models provided greater understanding the turbulent characteristics of amphibious UAV in predicting the drag force. The following are the general equations used to solve the turbulent models [19].…”

Section: Moving Reference Framementioning

confidence: 99%

Aerodynamic Interaction Studies on Amphibious Vehicle in Forward and Hovering Flight

Vikram¹,

Esakki²,

Manova³

et al. 2019

IJAME

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Unmanned aerial vehicles (UAVs) have gained a lot of attention in recent times due to its versatility in deployment for multifaceted operations. The development of amphibious UAVs with inculcating the features of hovercraft and multi-rotor has tremendous impact on military, naval and coastal guard applications. Stability and performance of this kind of vehicle highly depend on aerodynamic interaction of multirotor with respect to various wind conditions. The present study focuses on performing computational fluid dynamic (CFD) analysis on examining the vortex formation, turbulent regimes, wake region, tip vortex formulation and ground effect.Preliminary flow analysis is performed to determine the angle of attack (AoA) and wind speed on which minimal drag is experienced by the amphibious structure. Further, analysis conducted through varying the relative velocity of the vehicle and changing the speed of the propellers. The pressure distribution across the fuselage and rotor surface predicted the stability of the vehicle. The ground effect is examined through varying the clearance between the vehicle and ground surface with respect to a multiplicity of rotor diameter. CFD analysis results suggested that at 5° AoA and 8.3 m/sec the designed amphibious vehicle yielded superior performance characteristics and stability.

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“…The panel method solves potential flow around aircraft configuration which, if one extends the problem with boundary layer solution near the walls, enables to solve most problems in the linear behavior of the aircraft. 8,9 By iterating induced velocities on fuselage and empennage caused by rotor wake, the coupled method is established through Neumann boundary condition, in which the rotor wake is described by the free-wake method, and the aerodynamic performance of fuselage and empennage is represented by the panel method.…”

Section: Introductionmentioning

confidence: 99%

A coupled free-wake/panel method for rotor/fuselage/empennage aerodynamic interaction and helicopter trims

Cao

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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A coupled free-wake/panel method to predict the rotor downwash aerodynamic interaction and helicopter trims is presented. Free-wake method was developed to analyze aerodynamics interference of rotor wake, based on lifting-surface theory and vortex method, which relates the core radius, span station, and circulation of initial tip vortex with the blade-bound circulation distribution, and eliminates the empirical parameters during rotor free wake analysis. Helicopter fuselage with empennage was discretized into source panels. The vortex line mirror method was adopted to account for wake acceleration phenomenon that resulted from the close interaction between rotor wake and fuselage surface. The rotor wake geometry and downwash simulations were investigated including comparisons with the available measured data. Combined with the helicopter flight dynamics model and embedded in the trim procedure, the free-wake/panel coupled method was applied to calculate the rotor wake and its interference on other components of a full-scale UH-60A rotorcraft in level flight. Comparisons among predictions, referenced results, and experimental results are made for rotor wake geometries, blade-bound vortex, blade tip vortex, rotor downwash velocity, and control stick positions, and encouraging results were obtained. To validate the present method, this paper discusses the fundamental formulation, the numerical algorithms, and the simulation results.

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Panel/full-span free-wake coupled method for unsteady aerodynamics of helicopter rotor blade

Cited by 12 publications

References 22 publications

Aerodynamic design and optimization of propellers for multirotor

Aerodynamic design and optimization of propellers for multirotor

Aerodynamic Interaction Studies on Amphibious Vehicle in Forward and Hovering Flight

A coupled free-wake/panel method for rotor/fuselage/empennage aerodynamic interaction and helicopter trims

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