Coupled flight dynamics and CFD – demonstration for helicopters in shipborne environment

Crozon, C.; Steijl, R.; Barakos, George N.

doi:10.1017/aer.2017.112

Cited by 41 publications

(20 citation statements)

References 48 publications

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“…It uses the in-house flow solver HMB3, and couples Computational Fluid Dynamic (CFD) and Computational Structural Dynamics (CSD). The core functionality of HMB3 is CFD, however its use has been extended in recent years to include whole engineering applications, including helicopter rotor aeroelasticity [17], propeller aeroacoustics [18], flight mechanics [19] and missile trajectory prediction [20].…”

Section: Computational Methodology: Hmb3mentioning

confidence: 99%

“…where i, j, k represent the cell index, W and R are the vector of conservative variables and flux residual respectively and V i, j,k is the volume of the cell i, j, k. Greater detail on the numerical techniques employed can be found within the previous investigations conducted using HMB3 [17][18][19][20][24][25][26][27]. Several turbulence models, of both URANS and hybrid LES/URANS families, are available in the HMB3 solver.…”

Section: Computational Fluid Dynamicsmentioning

confidence: 99%

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High-Fidelity Computational Fluid Dynamics Methods for the Simulation of Propeller Stall Flutter

et al. 2019

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Brown, N. (2019) Highfidelity computational fluid dynamics methods for the simulation of propeller stall flutter. A time-marching aeroelastic method developed for the study of propeller flutter is presented and validated. Propeller flutter can take many forms with stall, whirl and classical flutter being the primary responses. These types of flutter require accurate capture of the non-linear aerodynamics associated with propeller blades. Stall flutter in particular needs detailed unsteady flow modelling. With the development of modern propeller designs potentially adjusting the flutter boundary and the development of faster computing power, CFD is required to ensure accurate capture of aerodynamics. Given the lack of reliable experimental stall flutter data for propellers, the method was focused on observing the correct qualitative behaviour with a comparison made between URANS and Scale-Adaptive Simulation (SAS). Greek α s m = Model amplitude of mode m of solid s (m/kg) ζ m = Damping coefficient (-) ρ = Fluid density (kg/m 3 ) ψ s m = Normalised m th mode displacement of solid s (m/kg) ψ s = Normalised displacement of solid s (m/kg) ω m = Natural frequency of mode m Ω CV = Control volume size Subscripts i, j, k = Mesh cell indices

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Section: Computational Methodology: Hmb3mentioning

confidence: 99%

Section: Computational Fluid Dynamicsmentioning

confidence: 99%

High-Fidelity Computational Fluid Dynamics Methods for the Simulation of Propeller Stall Flutter

et al. 2019

View full text Add to dashboard Cite

show abstract

“…where i, j, k represent the cell index, W and R are the vector of conservative variables and flux residual respectively and V i,j,k is the volume of the cell i,j,k. Greater detail on the numerical techniques employed can be found within the previous investigations conducted using HMB3 (12,13,14,20,21,22,23,24) . Several turbulence models, of both URANS and hybrid LES/URANS families, are available in the HMB3 solver.…”

Section: Computational Fluid Dynamicsmentioning

confidence: 99%

Estimation of three-dimensional aerodynamic damping using CFD

Higgins

Barakos

Jinks³

2019

Aeronaut. j.

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Aeroelastic phenomena of stall flutter are the result of the negative aerodynamic damping associated with separated flow. From this basis, an investigation has been conducted to estimate the aerodynamic damping from a time-marching aeroelastic computation. An initial investigation is conducted on the NACA 0012 aerofoil section, before transition to 3D propellers and full aeroelastic calculations. Estimates of aerodynamic damping are presented, with a comparison made between URANS and SAS. Use of a suitable turbulence closure to allow for shedding of flow structures during stall is seen as critical in predicting negative damping estimations. From this investigation, it has been found that the SAS method is able to capture this for both the aerofoil and 3D test cases.

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“…Not surprisingly, maneuvering for safe landing onboard a ship is a complex problem since the rotor flow field, wake, and unsteady aerodynamic loads are altered by the presence of the ship deck, and ship wake. The pilot workload during helicopter shipboard landing and take-off is then significantly increased [1][2][3]. Moreover, during flight operations, especially for take-off and landing, numerous factors expose flight and ground crew to substantial risks [4].…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the aerodynamic interaction between a tiltrotor and a tandem rotor during shipboard operations

Tan

Zhou

Sun

et al. 2019

Aerospace Science and Technology

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Numerical investigation of the aerodynamic interaction between a tiltrotor and a tandem rotor during shipboard operations.Abstract: Complex rotorcraft-to-rotorcraft interference problems occur during shipboard operations, and have a negative impact on safety. A vortex-based approach is used here to investigate the flow field and unsteady airloads of a tiltrotor affected by the wake of an upwind tandem rotor. In this work, the blade aerodynamics is modelled using a panel method, and the unsteady behavior of rotor wakes is modelled using a vortex particle method. The effects of the ship and sea-surfaces are accounted for via a viscous boundary model. The method is applied to a 1/48 th scaled model of a CH-46 operating on a model-scale Landing Helicopter Assault ship. The predicted vertical velocities at the location of the downstream V-22 are compared with Computational Fluid Dynamics and experiments carried out at NASA Ames Research Center. The results show that the predicted vertical velocities compare reasonably well with experiments and Computational Fluid Dynamics. A V-22 tilt-rotor placed in the wake of the CH-46 is also simulated, and rolling moments of the V-22 are calculated to show the effect of the upstream CH-46 wake. Keywords: rotorcraft-to-rotorcraft interference; flow field; shipboard operation; vortex particle method; viscous boundary model Nomenclature b, f = edge lengths of a rectangular panel, m b v = the V-22 wing span, m p C = pressure coefficient, dimensionless C P = rotor power coefficient, dimensionless 1 Lecturer, JianfengTan@njtech.edu.cn.

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Coupled flight dynamics and CFD – demonstration for helicopters in shipborne environment

Cited by 41 publications

References 48 publications

High-Fidelity Computational Fluid Dynamics Methods for the Simulation of Propeller Stall Flutter

High-Fidelity Computational Fluid Dynamics Methods for the Simulation of Propeller Stall Flutter

Estimation of three-dimensional aerodynamic damping using CFD

Numerical investigation of the aerodynamic interaction between a tiltrotor and a tandem rotor during shipboard operations

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