A computational fluid dynamic acoustic investigation of a tiltwing eVTOL concept aircraft

Higgins, Ross J.; Barakos, George N.; Shahpar, Shahrokh; Tristanto, Indi

doi:10.1016/j.ast.2021.106571

Cited by 25 publications

(2 citation statements)

References 30 publications

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“…There has been an abundance of new and novel aircraft designs [1][2][3][4] created for UAM in recent years. Several conceptual designs or prototypes have been unveiled by manufacturers such as Rolls-Royce [5], Uber [6], Airbus and Volocopter GmbH. Volocopter GmbH has introduced a very promising concept, the VC2X, featuring 18 rotors [7].…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Thrust Performance of a Small-Scale Staggered Rotor System in Hover

Zhu,

Deng,

Wei

et al. 2023

Drones

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In recent years, the demand for Urban Air Mobility (UAM) and Micro Aerial Vehicles (MAVs) has driven the emergence of new aircraft designs, with the Staggered Rotor System being widely applied in these vertical take-off and landing aircraft. Due to the complex aerodynamic interference between rotors, the spacing between them has a significant impact on the performance of these new aircraft configurations. A testbed was designed and validated to investigate the effects of parameters such as axial distance and lateral distance between rotors on the thrust performance of the Staggered Rotor System. A series of systematic thrust tests was conducted on two co-rotating small-scale rotor models, with particular focus on thrust testing of individual rotors in isolation and their comparison to the conditions of the Staggered Rotor System. During the experimental process, as both the axial and lateral distance varied, an orthogonal experimental design was employed to assess the influence of aerodynamic interactions caused by different rotor diameters on rotor performance. This study conducts an analysis of experimental data to investigate the influence of these factors on the performance of rotor systems’ thrust, while also examining the aerodynamic interference and aerodynamic force evolution patterns of rotor systems under varying parameters. Furthermore, rotor speed also plays a crucial role in the performance of the system. Therefore, when designing vertical take-off and landing aircraft with multiple rotors, it is essential to consider the influence of these factors during the optimization process.

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Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Thrust Performance of a Small-Scale Staggered Rotor System in Hover

Zhu,

Deng,

Wei

et al. 2023

Drones

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“…In response to the demand for high-speed cruise and vertical takeoff and landing (VTOL) capabilities, many new configurations aircraft [1][2][3] have been developed and the related aerodynamic characterization studies 4,5 have been conducted. The propulsive wing 6,7 vehicle is a new concept vehicle that has emerged over the last decade.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on aerodynamic characteristics of two-dimensional propulsive wing in cruise and hover

Wang

et al. 2022

International Journal of Micro Air Vehicles

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The propulsive wing vehicle is a new concept vehicle, which is driven by a cross-flow fan (CFF) embedded in the trailing edge of the wing. The propulsive wing vehicle is capable of cruising and hovering at high angles of attack with very high aerodynamic force coefficients, and has the potential to become a new type of vertical take-off and landing (VTOL) vehicle. The cruise and hover states of the propulsive wing vehicle are defined, and a numerical model of the two-dimensional propulsive wing is established. Based on the computational fluid dynamics (CFD) method, the rotation of the CFF is simulated by using the sliding mesh technique. The effects of cruise speed, angle of attack and CFF rotation speed on the aerodynamics of the two-dimensional propulsive wing are evaluated, and the mechanism of the propulsive wing flow field changes is revealed. The results show that the propulsive wing has a very high lift coefficient of up to 60 at low speed and high angle of attack cruise, and a high thrust coefficient of up to 40 at low speed and small angle of attack cruise. The aerodynamic force of the propulsive wing fluctuates periodically with the rotation of the CFF, and the amplitude of the fluctuation is related to the vorticity of the CFF blade shedding vortex. In hover, the flow field of the propulsive wing is affected by the geometry and wake deflection into an asymmetric distribution, forming a vortex on each side of the airfoil, and the vortex diameter varies with the CFF rotation speed, which in turn has an impact on the hovering performance of the propulsive wing.

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Aerodynamic Investigation of a New Layout for eVTOL Aircraft

Chen,

Chow,

Qiao

2024

2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings

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A computational fluid dynamic acoustic investigation of a tiltwing eVTOL concept aircraft

Cited by 25 publications

References 30 publications

Experimental Investigation on Thrust Performance of a Small-Scale Staggered Rotor System in Hover

Experimental Investigation on Thrust Performance of a Small-Scale Staggered Rotor System in Hover

Numerical study on aerodynamic characteristics of two-dimensional propulsive wing in cruise and hover

Aerodynamic Investigation of a New Layout for eVTOL Aircraft

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