Tiltrotor CFD Part I - validation

Jiménez-García, Antonio; Barakos, George N.; Gates, S. B.

doi:10.1017/aer.2017.17

Cited by 12 publications

(10 citation statements)

References 35 publications

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“…Using 512-544 cores, the simulations took ∼ 14 days (wall-time) to compute. The HMB3 solver has been validated for a wide range of complex flow cases [19,28,29]; however, to ensure the validity under the current case, the solver has been compared against available experimental data for a scale CROR.…”

Section: B the Hmb Solver And Cfd Simulationmentioning

confidence: 99%

Acoustic Analysis of Counter-Rotating Open Rotors with a Locked Blade Row

2020

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Counter Rotating Open Rotors (CROR) have the potential to reduce environmental emissions thanks to their high propulsive efficiency. However, there are a number of concerns surrounding their acoustic emissions. This contribution presents a novel multi-configuration CROR that offers considerable noise reductions. In particular, we consider locking either fore or aft rotor during takeoff , with the running rotor providing the required thrust. During cruise, both rotors are operated to retain the high efficiency of the CROR. A coupled Computational Fluid Dynamics-Computational Aeroacoustics analysis (CFD-CAA) has shown the potential of this multi-configuration concept to offer substantial noise reductions when compared to a baseline CROR. During a simulated constant-altitude flyover at takeoff conditions, reductions of 3.5 dBA and 7.9 dBA have been demonstrated when either fore or aft row is locked, respectively. Using the EPNL metric, this result corresponded to7 EPNLdB and 12 EPNLdB, respectively, for the same flyover.

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Section: B the Hmb Solver And Cfd Simulationmentioning

confidence: 99%

Acoustic Analysis of Counter-Rotating Open Rotors with a Locked Blade Row

2020

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“…In particular, the test case considered in the present work is the XV-15 aircraft due to the accessible and comprehensive data available in the literature. Indeed, this vehicle was commonly considered as a reference to validate fluid dynamics code for tiltrotor applications, as achieved, for example, by Garcia et al [32]. The numerical activity performed with DUST considered the steady-state conditions of the complete XV-15 tiltrotor aircraft in hover, conversion, and cruise conditions to be compared with the recent results that were obtained with the URANS CFD solver presented in the works by Tran et al [16,17].…”

Section: Introductionmentioning

confidence: 99%

Assessment of a Mid-Fidelity Numerical Approach for the Investigation of Tiltrotor Aerodynamics

et al. 2021

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The study of the complex aerodynamics that characterise tiltrotors represents a challenge for computational fluid dynamics tools. URANS numerical solvers are typically used to explore the aerodynamic features that characterise the different flight conditions of these aircraft, but their computational cost limits their applications to a few vehicle configurations. The present work explores the capabilities of a new mid-fidelity aerodynamic code that is based on the vortex particle method, DUST, to investigate the performance and flow physics of tiltrotors. With this aim, numerical simulations were performed in DUST while considering XV-15 tiltrotor configurations with increasing complexity. The study started with the investigation of a simpler configuration made up of a single wing and a proprotor. Subsequently, the full aircraft was studied in steady-level flights and its major operating flight conditions were explored—i.e., hover, conversion phase, and cruise. A thorough assessment of the code capabilities was performed by the comparison of the numerical results with high-fidelity Computational Fluid Dynamics (CFD) data. This thorough comparison showed that the mid-fidelity numerical approach implemented in DUST is suitable for capturing the flow physics related to the complex aerodynamic interactions between the proprotors and the wing along with the entire flight envelope of the tiltrotor. Moreover, a good representation of the aerodynamic performance of the vehicle was obtained, particularly for the flight conditions that are characterised by limited flow separations. The good accuracy obtained for both the performance and flow physics, combined with the relatively lower computational costs required by the mid-fidelity solver with respect to the URANS simulations, indicates that DUST could be considered a valuable tool for use in the preliminary design of novel tiltrotor configurations.

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“…Good agreement in terms of aerodynamics, acoustics and aeroelasticity were seen by all [12][13][14][15]. In addition to propeller flows, HMB3 has also been validated for tiltrotors, including the AW609 and XV-15 [16], for hover and forward flight. Further validation was conducted on a model scale propeller which was experimentally studied by Rolls-Royce.…”

Section: Hmb3mentioning

confidence: 86%