PhD Candidate: Edoardo Grande Aeroacoustic study of low ...
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Aeroacoustic study of low-Reynolds propellers for UAV applications PhD Candidate: Edoardo Grande Department: AWEP Section: Wind Energy Supervisors: Dr. F.Avallone, Dr. D. Ragni Promotor: Prof. dr. D. Casalino Contact: [email protected] Nowadays, UAVs (Unmanned Aerial Vehicle) are developing incredibly fast, both for military and commercial applications. The use of UAVs can be limited by their noise generation levels. Either for acoustic furtivity in military operations, or noise pollution in civilian use in proximity of populated areas, noise reduction of UAV propellers is a goal to achieve. Rotor noise is a key parameter also for PAVs (Personal Aerial Vehicles), an innovative transport mode that represents a solution to provide fast urban on-demand mobility. A electrical vertical take- off and landing (eVTOL) concept of PAV developed by 3DS is shown in Fig. 1. High fidelity CFD simulations represent a potential solution to better understand low Reynolds number flows, typical of small UAV propellers. To this aim, the software PowerFLOW will be used, which is based on a Lattice-Boltzmann method. Figure 3. Iso-surface of vorticity magnitude of a rotor in hover (LBM data). Aerodynamic and aeroacoustic measurements will be carried out in the Anechoic Wind Tunnel at TU Delft. A test-rig for UAV propeller (Fig. 4) has been designed. The test- rig is embedded with an electric motor, an encoder, a load cell and a torque cell. Figure 4. Left: Test-rig mounted in the A-Tunnel. Right: CAD of the test-rig. References: [1] D. Casalino, W. C. P. Van der Velden, G. Romani, “Community Noise of Urban Air Transportation Vehicles”. [2] M. McCrink and J. W. Gregory, “Blade Element Momentum Modelling of Low-Re Small UAS Electric Propulsion Systems”. [3] J. E. F. Williams and D. L. Hawkings, “Sound Generation by Turbulence and Surfaces in Arbitrary Motion”. High-fidelity simulations Low-fidelity tools Experimental testing Research context Figure 1. Electrical vertical take-off and landing PAV developed by 3DS [1]. Figure 2. Blade diveded in several sections for BEMT computation. 1 2 3 4 Aerodynamic: Blade Element Momentum Theory (BEMT) has been chosen [2]. Acoustic: Ffowcs Williams and Hawkings (FW-H) analogy [3] is used for the tonal part of noise. A trailing edge broadband model is added to enrich the acoustic prediction.
Transcript of PhD Candidate: Edoardo Grande Aeroacoustic study of low ...
Aeroacoustic study of low-Reynolds propellers for UAV applications
PhD Candidate: Edoardo GrandeDepartment: AWEPSection: Wind EnergySupervisors: Dr. F. Avallone, Dr. D. RagniPromotor: Prof. dr. D. CasalinoContact: [email protected]
Nowadays, UAVs (Unmanned Aerial Vehicle) are developingincredibly fast, both for military and commercial applications. Theuse of UAVs can be limited by their noise generation levels. Eitherfor acoustic furtivity in military operations, or noise pollution incivilian use in proximity of populated areas, noise reduction ofUAV propellers is a goal to achieve.Rotor noise is a key parameter also for PAVs (Personal AerialVehicles), an innovative transport mode that represents a solutionto provide fast urban on-demand mobility. A electrical vertical take-off and landing (eVTOL) concept of PAV developed by 3DS isshown in Fig. 1.
High fidelity CFD simulations represent a potential solutionto better understand low Reynolds number flows, typical ofsmall UAV propellers. To this aim, the software PowerFLOWwill be used, which is based on a Lattice-Boltzmann method.
Figure 3. Iso-surface of vorticity magnitude of a rotor in hover (LBM data).
Aerodynamic and aeroacoustic measurementswill be carried out in the Anechoic WindTunnel at TU Delft. A test-rig for UAVpropeller (Fig. 4) has been designed. The test-rig is embedded with an electric motor, anencoder, a load cell and a torque cell.
Figure 4. Left: Test-rig mounted in the A-Tunnel. Right:CAD of the test-rig.
References:[1] D. Casalino, W. C. P. Van der Velden, G. Romani, “Community Noise of Urban Air TransportationVehicles”.[2] M. McCrink and J. W. Gregory, “Blade Element Momentum Modelling of Low-Re Small UAS ElectricPropulsion Systems”.[3] J. E. F. Williams and D. L. Hawkings, “Sound Generation by Turbulence and Surfaces in ArbitraryMotion”.
High-fidelity simulationsLow-fidelity tools
Experimental testing
Research context
Figure 1. Electrical vertical take-off and landing PAV developed by 3DS [1].
Figure 2. Blade diveded in several sections for BEMT computation.
1 2 3 4
Aerodynamic: Blade Element Momentum Theory (BEMT)has been chosen [2].Acoustic: Ffowcs Williams and Hawkings (FW-H) analogy[3] is used for the tonal part of noise. A trailing edgebroadband model is added to enrich the acousticprediction.
