Simulation and Sensitivity Analysis of a Wing-Tip Mounted Propeller Configuration from the Workshop for Integrated Propeller Prediction (WIPP)

Zhou, Beckett Yx; Morelli, Myles; Gauger, Nicolas R.; Guardone, Alberto

doi:10.2514/6.2020-2683

Cited by 8 publications

(4 citation statements)

References 18 publications

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“…SU2 has also been extensively used for rotorcraft simulations [14]. In the Workshop for Integrated Propeller Prediction, SU2 has been used to model the turbulent flow field around a wing-tip mounted propeller design [15]. An interesting feature is the possibility of recasting the flow equations in a rotating reference system.…”

Section: B Su2: High-fidelity Aerodynamic Simulationsmentioning

confidence: 99%

Multi-Fidelity Numerical Approach to Aeroacoustics of Tandem Propellers in eVTOL Airplane Mode

Caccia

Abergo

Savino

et al. 2023

AIAA AVIATION 2023 Forum

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The present paper deals with an innovative multi-fidelity framework for characterizing the aerodynamics and the aeroacoustics of multirotor systems with application to advanced eVTOL aircraft. In this framework, the goal of the activity is a multi-fidelity investigation of two propellers in tandem with rotor disks overlap, reproducing a typical feature of eVTOL architectures in airplane mode flight conditions. A Ffowcs Williams-Hawkings equation solver is used to compute the aeroacoustic footprint of the test case in different configurations. The solver is run with both mid-fidelity aerodynamic simulation data obtained with DUST and high-fidelity simulation data obtained with SU2. The comparison between the two different approaches highlights the suitability of the DUST mid-fidelity simulations for the aeroacoustic investigation of a propeller in airplane mode configuration with a much lower computational cost with respect to high-fidelity CFD simulations. On the other hand, the co-axial propellers tandem configuration shows some differences in the sound pressure level computed with the two approaches, mainly due to the contribution to noise emission given by the rear propeller.

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Section: B Su2: High-fidelity Aerodynamic Simulationsmentioning

confidence: 99%

Multi-Fidelity Numerical Approach to Aeroacoustics of Tandem Propellers in eVTOL Airplane Mode

Caccia

Abergo

Savino

et al. 2023

AIAA AVIATION 2023 Forum

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“…Suitable refinement is important to reduce numerical dissipation of the wake so that blade-tip vortex/wing interaction effects are correctly modeled. The importance of the mesh refinement region in the near-field propeller wake around the nacelle was previously presented by Zhou et al 4 Based on this work, details of the grid selected for this study are outlined in Table 3.…”

Section: Ivb Mesh Generationmentioning

confidence: 99%

“…A critical first stage of this work was the simulation of the aerodynamics of the WIPP configuration in order to assess the numerical prediction capabilities of the open-source SU2 solver. 4 In order to evaluate the numerical prediction capabilities, quantities including the pressure coefficient distribution along different stations of the wing and wake data were compared with measurements from the experimental database. In the main, the numerical predictions were shown to be in good agreement with the experimental measurements.…”

Section: Introductionmentioning

confidence: 99%

Aeroacoustic Analysis of a Wing-Tip Mounted Propeller Configuration

Zhou

Morelli

Guardone

et al. 2021

Aiaa Aviation 2021 Forum

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This work focuses on analysing the turbulent flow-field an d no ise of a wi ng-tip mo unted pr opeller configuration using the model and test conditions released by the Workshop for Integrated Propeller Prediction (WIPP). In particular, the unsteady Reynolds-averaged Navier-Stokes and enhanced delayed detached eddy simulations with Spalart-Allmaras turbulence model are performed in a time-accurate manner. A multi-zone sliding mesh technique is used to allow for the relative motion of the propeller with the stationary wing. Timeaveraged pressure coefficients at four spanwise locations along the wing surface are evaluated and shown to be in good agreement with the experimental data, including the two locations directly in the propeller slipstream. The simulations reveal two major noise sources of this wing-tip mounted propeller configuration, namely the turbulent wake and tip vortex generated by the propeller blades, which both impinge on the wing and nacelle surfaces as they convect downstream. Visualization of the surface pressure fluctuations at 6 different operating conditions with varying Mach number and angle-of-attack reveals the noise footprints on this integrated propeller-wing system. In particular, the impingement of propeller blade tip vortices on the leading edge of the wing towards the nacelle is identified to be the dominant noise s ource. This is confirmed by the farfield noise computation for observers located on the azimuthal propeller plane and the fly-over plane, which reveals that at most observer angles, especially the side-line ones, the unsteady loading on the wing and nacelle surfaces represents the dominant noise source.

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“…It should be noted that in the current implementation the eddy viscosity is frozen, leaving out the terms originating from the turbulence model equations. The derivation of the adjoint boundary conditions leads to an expression having a similar form as the flow boundary conditions (5).…”

Section: Adjoint Problemmentioning

confidence: 99%

Unsteady Adjoint Method for Aeroacoustic Propeller Optimization

Soemarwoto

Ven

Kok

et al. 2021

Aiaa Aviation 2021 Forum

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The development of an adjoint method for design optimization of a propeller in an unsteady flow field is presented. The methodology follows the continuous-discrete approach, where the adjoint equations are formulated in a continuous form and afterwards discretized in the same way as the flow equations are discretized. The time-dependent flow and adjoint equations are solved respectively to determine the aeroacoustics performance and gradients of the functionals. The aerodynamic characteristics are obtained using NLR's CFD solver ENSOLV, while the acoustic characteristics are calculated using the Ffowcs Williams and Hawkings equation. Two aspects are highlighted, namely the development and verification of (i) the unsteady adjoint solver and (ii) the adjoint phase-lagged boundary condition. Computational results are presented for test cases ranging from an academic single airfoil to an industrially relevant propeller configuration.

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Simulation and Sensitivity Analysis of a Wing-Tip Mounted Propeller Configuration from the Workshop for Integrated Propeller Prediction (WIPP)

Cited by 8 publications

References 18 publications

Multi-Fidelity Numerical Approach to Aeroacoustics of Tandem Propellers in eVTOL Airplane Mode

Multi-Fidelity Numerical Approach to Aeroacoustics of Tandem Propellers in eVTOL Airplane Mode

Aeroacoustic Analysis of a Wing-Tip Mounted Propeller Configuration

Unsteady Adjoint Method for Aeroacoustic Propeller Optimization

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