Experimental study of a helicopter rotor model in hover

Panayotov, Filip; Dobrev, Ivan; Massouh, Fawaz; Todorov, Milcho

doi:10.1051/matecconf/201823401002

Cited by 11 publications

(4 citation statements)

References 7 publications

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“…The calculation model was constructed by using solidworks software combined with airfoil data published by NASA [6]. Firstly, profili was used to derive airfoil data, and the airfoil surface was formed according to the upper and lower airfoil data, and the body was formed by stretching.…”

Section: Rotor Modelmentioning

confidence: 99%

“…RANS applies the statistical theory of turbulence to average the time interval of the non-stationary N-S equation and solve the time mean required in engineering. This method is a common numerical simulation method for complex turbulence in engineering [6]. The time calculation of the nonstationary N-S equation is done and the Reynolds equation is obtained by using the Boussinesp hypothesis…”

Section: Rans Turbulence Simulationmentioning

confidence: 99%

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Research on finite element model of rotor aerodynamicnoise in hovering state

Huang,

Yang,

Sun

et al. 2024

J. Phys.: Conf. Ser.

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The helicopter has been widely used in many fields, and the rotor aerodynamic noise has gradually attracted attention. The non-homogeneous wave equation, Ffowcs Williams-Hawkings equation (FW-H equation) derived from hydrodynamic N-S equation, combined with RANS turbulence simulation, was used to simulate the sound field of NACA0012 airfoil-shape model in hovering state. On this basis, by changing the thickness and camber of the blade, the aerodynamic noise of the rotor under different airfoil profile thickness and camber is calculated. The results show that the change of airfoil thickness and camber will affect the aerodynamic noise of the rotor in hovering state.

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Section: Rotor Modelmentioning

confidence: 99%

Section: Rans Turbulence Simulationmentioning

confidence: 99%

Research on finite element model of rotor aerodynamicnoise in hovering state

Huang,

Yang,

Sun

et al. 2024

J. Phys.: Conf. Ser.

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show abstract

“…The blade is constructed by the Solidworks module and combined with the airfoil data [11] released by NASA. The airfoil data is derived by profile and the airfoil surface is formed according to the airfoil data.…”

Section: Establishment Of Rotor and Fuselage Modelsmentioning

confidence: 99%

Numerical simulation of the effect of helicopter flight advance ratio and lift rate on rotor aerodynamic noise

Huang,

Sun,

Yang

et al. 2024

J. Phys.: Conf. Ser.

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To study the aerodynamic noise characteristics of helicopter rotors under different flight states, this paper combined with the FW-H calculation equation, adopted NACA0012 airfoil and ROBIN fuselage to form a helicopter model and used FLUENT software to simulate different flight states of the helicopter. The influence of the two flight parameters, advance ratios, and lift rates, on the aerodynamic noise characteristics of the rotor, is studied. The results show that with the increase of helicopter advance ratio, the aerodynamic noise generated by the rotor becomes larger, and the effect of helicopter lift rate on the aerodynamic noise of the rotor is not obvious.

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“…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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Experimental study of a helicopter rotor model in hover

Cited by 11 publications

References 7 publications

Research on finite element model of rotor aerodynamicnoise in hovering state

Research on finite element model of rotor aerodynamicnoise in hovering state

Numerical simulation of the effect of helicopter flight advance ratio and lift rate on rotor aerodynamic noise

Variable Pitch Propeller for UAV-Experimental Tests

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