Rotor Blade Performance Analysis with Blade Element Momentum Theory

Mahmuddin, Faisal

doi:10.1016/j.egypro.2017.03.477

Cited by 70 publications

(33 citation statements)

References 2 publications

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“…The rotor model used in flight simulation is mainly based on blade element-momentum theory, which can calculate the thrust and torque of the rotor with acceptable accuracy when the rotor receives mainly axial flow-the flow is nearly perpendicular to the rotor rotational plane. [4][5][6] However, when the Quad-Plane is subject to wind disturbance, the direction of wind disturbance is approximately parallel to the ground in most engineering applications, and the rotor receives the influence of the oblique flow and will also generate nonnegligible forces and moments in rotational plane. 5,7,8 In order to calculate the aerodynamic performance of the rotor in such an oblique flow in flight simulation, an accurate and efficient method is required.…”

Section: Introductionmentioning

confidence: 99%

Dynamic modeling, simulation, and parameter study of electric quadrotor system of Quad-Plane UAV in wind disturbance environment

Song

et al. 2021

International Journal of Micro Air Vehicles

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Quad-Plane UAV(quadrotor fixed-wing hybrid vertical take-off and landing Unmanned Aerial Vehicle) is vulnerable to wind disturbance in quadrotor mode, and the performance of the electric quadrotor system directly affects its wind disturbance rejection performance. To study and optimize the wind disturbance rejection performance of the electric quadrotor system of Quad-Plane precisely and efficiently, a dynamic electric quadrotor simulation system integrating high-precision submodels of electric quadrotor system components is required. However, there are few papers on this kind of simulation system. This paper proposed a simulation system with both high computational efficiency and precision, and it can be used in optimization and flight simulation of Quad-Plane. The simulation system includes submodels of rotor, brushless direct current (BLDC) motor, electronic speed controller (ESC), and Li-ion Polymer battery. The surrogate-based rotor model is established to calculate the aerodynamic performance of the rotor in oblique flow. The BLDC motor performance calculation model considering inductance is presented and the power loss of the ESC is considered. The discharge characteristics of the battery are modeled considering the rate capacity effect. All submodels are validated and the simulation results show good agreements with test data. A flight test of Quad-Plane in quadrotor mode is conducted to validate the integrated dynamic simulation system. The results show that the simulation system has the advantages of high computational efficiency and precision. Based on the simulation system, the influence of the electric quadrotor system parameters on the performance of the electric quadrotor system, and furthermore on the wind disturbance rejection performance of the Quad-Plane are found, the conclusions are helpful to the selection and optimization of the electric quadrotor system components.

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Section: Introductionmentioning

confidence: 99%

Dynamic modeling, simulation, and parameter study of electric quadrotor system of Quad-Plane UAV in wind disturbance environment

Song

et al. 2021

International Journal of Micro Air Vehicles

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“…Considering the importance of exploiting renewable energy resources in recent decades, the blade shape for a wind turbine can be optimized by finding the best combination of airfoil type, chord length, and twist angle with the highest local torque along the spanwise direction of the blade [7,8]. Therefore, for prompt design evaluation using blade element momentum (BEM) theory, the aerodynamic lift and drag coefficients used in BEM theory-based calculations are required, depending primarily on 2D wind tunnel measurements of airfoils with a constant span.…”

Section: Introductionmentioning

confidence: 99%

Characteristics and Effects of Laminar Separation Bubbles on NREL S809 Airfoil Using the γ - R e θ Transition Model

Rho

2020

Applied Sciences

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Understanding the characteristics and effects of the laminar separation bubbles (LSBs) is important in the aerodynamic design of wind turbine airfoils for maximizing wind turbine efficiency. In the present study, numerical simulations using the γ-Reθ transition model were performed to analyze the flow structure of LSBs around a 21% thick NREL S809 airfoil. The simulation results obtained from the γ-Reθ transition model and the standard k-ε model for the aerodynamic coefficients at various angles of attack (AoAs) were compared with the wind tunnel data acquired from the Delft University 1.8 m × 1.25 m low-turbulence wind tunnel. When the AoA increased, the bubble on the suction airfoil surface was found to move closer to the leading edge owing to an earlier laminar separation (LS). Furthermore, the transition onset (TO) points were shown to occur right after separation, thus causing an abrupt increase in turbulence intensity (TI) and forming different bubble extents with increasing AoAs. Consequently, the transition model-based approaches can provide a clear understanding of the characteristics and effects of the LSB on airfoil aerodynamic performance. The findings of this study can provide important insights into redesigning an airfoil with a reduced bubble length causing the improved aerodynamic performance.

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“…1,2 The elasticity of the material affects the blade's deformation during the rotation; a lighter material with higher elastic modulus is required to ensure that the impact of the airfoil vortex leads downward to obtain an optimal thrust value. Momentum and blade element theory [3][4][5] can be used in propeller's performance analysis. Depending on the propeller's structure, the magnitude of the generated thrust depends, among others, on the number of blades, propeller diameter, the angle of attack or pitch angle, and the speed of the propeller.…”

Section: Introductionmentioning

confidence: 99%

Analysis of quadcopter propeller vibration based on laser vibrometer

Kuantama

Moldovan

Ţarcă

et al. 2019

Journal of Low Frequency Noise, Vibration and Active Control

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An unbalanced propeller can affect a quadcopter's performance due to vibration, also decreasing its thrust's yield. Analyses were conducted to determine the correlation between vibration in the dynamic movement of a balanced and an imbalanced propeller using a laser vibrometer (portable digital vibrometer) PDV-100, to determine the correlation between propeller rotational speed and its vibration, as well as to determine the propeller's maximum rotational speed to avoid over-vibration. The vibration analysis was conducted on a carbon fiber 2-blade propeller by comparing the results of vibration tests with the propeller blade contour. The vibration response of the propeller has been analyzed at three points, respectively the hub, the center, and the tip of the blade, to determine the point having the largest value of the vibration on the propeller running at a maximum rotation speed of 7000 rpm. The same analysis was made on two propellers: the first one of type 1340 with a diameter of 13 inches and the second one of type 1447 with a diameter of 14 inches. The vibration was reduced by propeller's static balancing, thus increasing the propeller stability. The result showed that an imbalanced propeller generated a decrease in the rotational speed and higher vibration values compared to the balanced propeller. The vibration values showed a linear dependency to the rotor speed; the higher the speed, the bigger the vibration. The limit of rotational speed for the balanced model of the 1340 type propeller was 5000 rpm whilst the corresponding value for the 1447 type propeller was 4500 rpm. Finally, the result was used to optimize the propeller's overall performance.

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Rotor Blade Performance Analysis with Blade Element Momentum Theory

Cited by 70 publications

References 2 publications

Dynamic modeling, simulation, and parameter study of electric quadrotor system of Quad-Plane UAV in wind disturbance environment

Dynamic modeling, simulation, and parameter study of electric quadrotor system of Quad-Plane UAV in wind disturbance environment

Characteristics and Effects of Laminar Separation Bubbles on NREL S809 Airfoil Using the γ - R e θ Transition Model

Analysis of quadcopter propeller vibration based on laser vibrometer

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