Effects of relative thickness on aerodynamic characteristics of airfoil at a low Reynolds number

Ma, Dongli; Zhao, Yanping; Qiao, Yuhang; Li, Guanxiong

doi:10.1016/j.cja.2015.05.012

Cited by 49 publications

(16 citation statements)

References 9 publications

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“…The main criteria to select an airfoil are [3,19,33,34] (1) provide the required lift and minimize the drag; (2) the maximum lift coefficient (C Lmax ) should be high to increase angle of attack causing stall; (3) the thickness of the airfoil (t) should be as thin as possible to avoid the formation of the laminar separation bubble (LSB) [35,36]. At the same time, to place some of the electrical components inside the wing, the maximum thickness of a MAV should be between 8 and 11 % of the chord.…”

Section: Determination Of the Characteristics Of The Wingmentioning

confidence: 99%

Design, manufacturing, and flight testing of a fixed wing micro air vehicle with Zimmerman planform

Hassanalian

Abdelkefi

2016

Meccanica

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An optimized and comprehensive method is used to design and manufacture a fixed wing micro air vehicle (MAV) with Zimmerman planform. The design process includes four stages which are the specification of the flight mission, determination of the best aspect ratio, identification of the optimum wing loading and thrust loading values, and estimation of the weight of the structural components of the MAV. To do this, various statistical and analytical methods are utilized. Based on an aerodynamic analysis, the results show that an optimum aspect ratio that maximizes the performance of the Zimmerman MAV for a well-defined cruise speed is determined. Considering six possible flights, a constraint analysis is performed and an optimum wing loading value is determined. It is shown that the computational method is beneficial to determine the exact masses for the structural components including the wing, fuselage, and vertical tail. Using the 3D panel method, the determination of the shape of the reflexed airfoil for the MAV is successfully done by minimizing the drag force and the angle of attack to use less powerful motor and avoid any stall effect, respectively. A stability analysis is then performed to check the safe flight of the designed vehicle. During test flight, the results show that the designed Zimmerman MAV satisfies the pre-defined specification. The final characteristics of the manufactured MAV are: wingspan of 44 cm, weight of 450 g, aspect ratio of 1.51, cruise speed of 20 m/s, and flight endurance of 20 min.

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Section: Determination Of the Characteristics Of The Wingmentioning

confidence: 99%

Design, manufacturing, and flight testing of a fixed wing micro air vehicle with Zimmerman planform

Hassanalian

Abdelkefi

2016

Meccanica

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“…Content may change prior to final publication. calculations [18]. In this study, the Reynolds averaged Navier-Stokes equations are solved using the γ-Reθ transition model from Menter and Langtry for closure [19].…”

Section: ) Radar Antenna Parameterizationmentioning

confidence: 99%

Integrated Optimization Approach for Aerodynamic, Structural, and Embedded Antenna Design of Joined-Wing SensorCraft

Jia

et al. 2020

IEEE Access

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The joined-wing configuration SensorCraft, presents a more feasible way to meet tough design requirements such as long-endurance and 360-deg radar coverage compared to conventional and flying wing configurations. Proper assessment of the interactions between aerodynamics, structure, and embedded antenna in the optimization of the joined-wing SensorCraft is essential to obtain superior performances. This paper establishes the embedded radar performance estimation model and describes an integrated design process of aerodynamic, structure, and embedded radar performance of such an aircraft. Results show that multi-objective optimization leads to an increase of 14.76% in lift-to-drag ratio, 3.96% and 8.75% in the forward-looking and backward-looking radar detection ranges respectively. Moreover, the structural weight is reduced by 6.0% compared to that of the baseline design. Moreover, sensitivities of the rear wing dihedral angle, endplate height ratio, and joint location of the joined-wing configuration are analyzed in detail.

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“…Due to the unavailability of experimental data in most of the real icing conditions, the accuracy of CFD predictions cannot always be validated. But there are some CFD studies [30][31][32][33][34] on iced aerofoils that have been validated with available experimental data. Their results show that a high-quality mesh is necessary, especially in the case of large horn ice shapes; as well as an appropriate turbulence model in addition to a transition model.…”

Section: Aerodynamic Characterization Of Iced Aerofoilsmentioning

confidence: 99%

Numerical Investigation of the Aeroelastic Behavior of a Wind Turbine with Iced Blades

et al. 2019

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Wind turbines installed in cold-climate regions are prone to the risks of ice accumulation which affects their aeroelastic behavior. The studies carried out on this topic so far considered icing in a few sections of the blade, mostly located in the outer part of the blade, and their influence on the loads and power production of the turbine are only analyzed. The knowledge about the influence of icing in different locations of the blade and asymmetrical icing of the blades on loads, power, and vibration behavior of the turbine is still not matured. To improve this knowledge, multiple simulation cases are needed to run with different ice accumulations on the blade considering structural and aerodynamic property changes due to ice. Such simulations can be easily run by automating the ice shape creation on aerofoil sections and two-dimensional (2-D) Computational Fluid Dynamics (CFD) analysis of those sections. The current work proposes such methodology and it is illustrated on the National Renewable Energy Laboratory (NREL) 5 MW baseline wind turbine model. The influence of symmetrical icing in different locations of the blade and asymmetrical icing of the blade assembly is analyzed on the turbine’s dynamic behavior using the aeroelastic computer-aided engineering tool FAST. The outer third of the blade produces about 50% of the turbine’s total power and severe icing in this part of the blade reduces power output and aeroelastic damping of the blade’s flapwise vibration modes. The increase in blade mass due to ice reduces its natural frequencies which can be extracted from the vibration responses of the turbine operating under turbulent wind conditions. Symmetrical icing of the blades reduces loads acting on the turbine components, whereas asymmetrical icing of the blades induces loads and vibrations in the tower, hub, and nacelle assembly at a frequency synchronous to rotational speed of the turbine.

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Effects of relative thickness on aerodynamic characteristics of airfoil at a low Reynolds number

Cited by 49 publications

References 9 publications

Design, manufacturing, and flight testing of a fixed wing micro air vehicle with Zimmerman planform

Design, manufacturing, and flight testing of a fixed wing micro air vehicle with Zimmerman planform

Integrated Optimization Approach for Aerodynamic, Structural, and Embedded Antenna Design of Joined-Wing SensorCraft

Numerical Investigation of the Aeroelastic Behavior of a Wind Turbine with Iced Blades

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