A simplified model for predicting the propeller-wing interaction

Huang, Xianghua; Zhao, Xiaochun; Huang, Jiaqin

doi:10.1108/aeat-06-2016-0102

Cited by 5 publications

(2 citation statements)

References 9 publications

(10 reference statements)

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“…Mieloszyk and Galinski (2013) have experimentally showed that the increase in lift of the UAV is not only caused by propeller in vertical direction, but it also depends upon some other factors such as flow on the wing. The aerodynamic characteristic of propeller-driven UAV is much depends on the propeller and wing flow interaction (Aref et al , 2018; Huang et al , 2018). The induced flow from the propeller has increased the free stream velocity above the wing and this situation will reduce the pressure distribution (Ahn and Lee, 2013; Chinwicharnam et al , 2015; Sudhakar et al , 2017).…”

Section: Introductionmentioning

confidence: 99%

Propeller locations study of a generic delta wing UAV model

Kasim¹,

Mat²,

Ishak³

et al. 2020

AEAT

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Purpose This study aims to investigate the effects of propeller locations on the aerodynamic characteristics of a generic 55° swept angle sharp-edged delta wing unmanned aerial vehicle (UAV) model. Design/methodology/approach A generic delta-winged UAV model has been designed and fabricated to investigate the aerodynamic properties of the model when the propeller is placed at three different locations. In this research, the propeller has been placed at three different positions on the wing, namely, front, middle and rear. The experiments were conducted in a closed-circuit low-speed wind tunnel at speeds of 20 and 25 m/s corresponding to 0.6 × 106 and 0.8 × 106 Reynolds numbers, respectively. The propeller speed was set at constant 6,000 RPM and the angles of attack were varied from 0° to 20° for all cases. During the experiment, two measurement techniques were used on the wing, which were the steady balance measurement and surface pressure measurement. Findings The results show that the locations of the propeller have significant influence on the lift, drag and pitching moment of the UAV. Another important observation obtained from this study is that the location of the propeller can affect the development of the vortex and vortex breakdown. The results also show that the propeller advance ratio can also influence the characteristics of the primary vortex developed on the wing. Another main observation was that the size of the primary vortex decreases if the propeller advance ratio is increased. Practical implications There are various forms of UAVs, one of them is in the delta-shaped planform. The data obtained from this experiment can be used to understand the aerodynamic properties and best propeller locations for the similar UAV aircrafts. Originality/value To the best of the author’s knowledge, the surface pressure data available for a non-slender delta-shaped UAV model is limited. The data presented in this paper would provide a better insight into the flow characteristics of generic delta winged UAV at three different propeller locations.

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Section: Introductionmentioning

confidence: 99%

Propeller locations study of a generic delta wing UAV model

Kasim¹,

Mat²,

Ishak³

et al. 2020

AEAT

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“…Other approaches based on potential methods and superposition of induced velocities but not using BEMT were tested, for exemple, by Chiocchia and Pignataro (1995), Fratello, Favier andMaresca (1991), andHuang, Zhao andHuang (2018), among other authors. In order to model distributed propulsion systems, Cole et al (2019) developed a high-order free-wake method for propeller-wing systems that was implemented using high-order vorticity elements distributed to represent the aircraft wing and the propeller blades.…”

Section: Methods For Aerodynamic and Aeroacoustic Modeling Of Install...mentioning

confidence: 99%

Experimental assessment of aerodynamic and aeroacoustic interaction effects of wingtip-mounted propellers

Silva

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Thanks to Prof. Dr. Fernando Martini Catalano, friend, and advisor, for all the trust, opportunities, and knowledge exchange over the years we have been working together. I want to thank the laboratory technicians Osnan Ignácio Faria, José Cláudio Pinto de Azevedo, and Fábio Luis Gallo for their friendship, solicitude, help, and shared knowledge in the manufacture, assembly, maintenance, and operation of the equipment and models necessary to carry out the experiments. Thanks to Prof. Dr. Érico Masiero, for lending the omnidirectional sound source. I want to thank

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Leading and Trailing Edge Configuration for Distributed Electric Propulsion Systems

Eqbal,

Marino,

Farley

2023

Sustainable Aviation

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In pusher-type aircraft, the impact of putting the propeller on the trailing edge and impact of propeller on the tip of the wing has been carefully researched. The results reveal an increase in propelling e ciency and a reduction in drag. In addition, there is a lot of study being done right now on distributed propulsion and the advantages it has in terms of aerodynamic effects and propelling advantages. This paves the way for the possibility of positioning the propeller on the trailing edge of the wing and using the increased propulsive e ciency afforded by boundary layer ingestion (BLI). This research studies the effect of positioning the propeller on the trailing edge of the wing instead of the leading edge on power savings and advances in propulsive e ciency. A scaled Remotely Piloted Aircraft Systems (RPAS) wing is tested in a wind tunnel utilising a Brushless Direct Current (BLDC) engine with several propeller con gurations. A new term, Ingestion Ratio (IR), is introduced to describe the effect of the change in propeller size on power savings. The investigation revealed that positioning the propeller on the trailing edge of the wing increases the propelling e ciency by up to 5.8% and saves up to 24.7% of electricity.

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A simplified model for predicting the propeller-wing interaction

Cited by 5 publications

References 9 publications

Propeller locations study of a generic delta wing UAV model

Propeller locations study of a generic delta wing UAV model

Experimental assessment of aerodynamic and aeroacoustic interaction effects of wingtip-mounted propellers

Leading and Trailing Edge Configuration for Distributed Electric Propulsion Systems

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