Experimental hover performance evaluation on a small-scale rotor using a rotor test stand

Lee, Byoung-Eon; Byun, Young-Seop; Kim, Jeong; Kang, Beom-Soo

doi:10.1007/s12206-011-0429-5

Cited by 11 publications

(3 citation statements)

References 2 publications

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“…Rotor operation over time can be analyzed by mathematical modeling, including simulation based on computational fluid dynamics (CFD) [6][7][8] as well as by experiments on a test stand [9] or in a wind tunnel [10,11]. The CFD method is also widely used in the analysis of steady-state aerodynamic interactions [12] and rotor wake geometry [13,14].…”

Section: Introductionmentioning

confidence: 99%

Numerical calculations of the autorotating rotor under transient conditions

Czyż¹,

Kazimierska²,

Karpiński

et al. 2021

J. Phys.: Conf. Ser.

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It is necessary to evaluate the performance of the main rotor in design stages of a rotorcraft to obtain the assumed lift force and low aerodynamic drag. This paper presents the CFD numerical analysis of the autorotating rotor under transient conditions. Auto-rotation is particularly important in the case of gyrocopters, while in the case of helicopters it is related to flight safety. The calculations allowed us to obtain aerodynamic forces and torque as a function of rotor azimuth for individual rotor blades. The analysis was performed for a rotor tilted by 15 degrees toward the airflow direction. A geometric model was created for the calculations and then a computational model was created in Ansys Fluent software. The k-ω SST model was adopted as the turbulence model which considers the turbulence kinetic energy and its unit dissipation. The obtained results are presented in a rotor and flow coordinate system.

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Section: Introductionmentioning

confidence: 99%

Numerical calculations of the autorotating rotor under transient conditions

Czyż¹,

Kazimierska²,

Karpiński

et al. 2021

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…The research also concerned noise generated by propellers [27] and propeller behavior in crosswinds [28]. Rotors with variable pitch blades, intended for drones, were tested for helicopters [29][30][31], but there are still no data for small rotors for small unmanned fixed-wing or multi-rotor drones. The main reason for this is that on the market there are no readily available mechanisms that allow for a change of the blade pitch in an effective way.…”

Section: Introductionmentioning

confidence: 99%

Variable Pitch Propeller for UAV-Experimental Tests

et al. 2020

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Growth in application fields of unmanned aerial vehicles (UAVs) and an increase in their total number are followed by higher and higher expectations imposed on improvements in UAV propulsion and energy management systems. Most commercial vertical takeoff and landing (VTOL) UAVs employ a constant pitch propeller that forces a mission execution tradeoff in the majority of cases. An alternative solution, presented here, consists of the use of a variable pitch propeller. The paper summarizes experimental measurements of the propulsion system equipped with an innovative variable pitch rotor. The investigations incorporated characteristics of the rotor for no wind conditions and a new approach to optimize pitch settings in hover flight as a function of UAV weight and energy consumption. As UAV battery capacity is always limited, efficient energy management is the only way to increase UAV mission performance. The study shows that use of a variable pitch propeller can increase the maximal takeoff weight of the aircraft and improve power efficiency in hover, especially if load varies for different missions. The maximal thrust measured was 31% higher with respect to the original blade settings. The coefficient of thrust during hover showed an increase of 2.6% up to 7.5% for various pitch angles with respect to the original fixed propeller.

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“…In [10] the authors evaluate the hover performance of a helicopter rotor. For this purpose a rotor test stand is built.…”

Section: Introductionmentioning

confidence: 99%

Experimental study of a helicopter rotor model in hover

et al. 2018

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This paper presents the results from an experimental study of the aerodynamic performance and efficiency of a model helicopter rotor in steady hover at Reynolds numbers below 70000. Results are shown for a two-, three- and four-bladed rotor configuration for various pitch angles and speeds of rotation. The influence of the rotor solidity on the aerodynamic efficiency in terms of the Figure of Merit is highlighted. The profile drag component is evaluated as a function of the Reynolds number. The internal friction losses of the test stand are estimated and taken into account in all measurements. A brief description of the designed test stand is provided. The experimental setup allows for the measurement of thrust and torque of helicopter rotors with diameters of up to 1 meter, for pitch angles varying from -12° to +24° and for rotational speeds of up to 3000 RPM. Conclusions are drawn about the aerodynamic performance and efficiency of the studied rotor configurations. This experimental study provided a significant database, which will serve for validation purposes.

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Experimental hover performance evaluation on a small-scale rotor using a rotor test stand

Cited by 11 publications

References 2 publications

Numerical calculations of the autorotating rotor under transient conditions

Numerical calculations of the autorotating rotor under transient conditions

Variable Pitch Propeller for UAV-Experimental Tests

Experimental study of a helicopter rotor model in hover

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