The main objective of this paper is to compare the aerodynamic characteristics for several span lengths and sweep angles and to find their most efficient combinations. Morphing wing analysis occurs at three selected locations that have been specified for extending and modifying span length by (25%, 50%, and 75%) of its original length to fulfill various flight mission requirements. The wing design is based on a NACA 4412 aerofoil with the root chord of 0.675m and the tip chord of 0.367m for the fixed segment and 0.320m for the moving segment. The proposed concept consists in the sliding of the inner section into the fixed part along the wing with varying the angle of the inner section inside the fixed part (parallel with the leading edge and the moving-wing axis is coincident to the fixed-wing axis) within two configurations. This work presents a comparative study of design and development, in addition, of analyses of variable span morphing of the tapered wing (VSMTW) for the unmanned aerial vehicle (UAV).
AIRFOIL DIAGRAM SOFTWARE
The software generated results when compared to the regression data generated ascertained to be in a good correlation with each other. On evaluating and considering the variable conditions, the optimum values are obtained for the aerofoil at 15° angle of inclination at an inlet velocity of 9 m/s. The further simulations and evaluations were executed using the Ansys Fluent software. The plot points for the geometries are generated using the Auto CAD for different angles. The inlet velocity for the flow along the surface of the aerofoil geometry was taken varied from 7.5 m/s to 10 m/s with 0.5 m/s interval for each model. This evaluation was done for the angle of attack ranging from 0° to 20° with 5° interval for each model. The aerofoil geometry was analysed for a constant angle of attack along the total length. The aerofoil geometries are opted to be of new aerofoil type of NACA 8412 series. The work is intended to focus on analysing the flow behaviour along the surface of the aerofoil geometry. The conception and examination for the aerofoil geometry have been executed in the current work to evaluate the behaviour of the flow in terms of the velocity and pressure lineation. The aerofoils which allow for the flow at a broader range of angles have a more significant impact on the power generation from the turbine. The study also extends to find an optimum ratio between wing and winglet. The study then continued with the wing span of 5m and 7m. It is found that the blade with winglet gives an L/D ratio of 13.8 compared to the one without winglet, 8.8, for a 3m wing span. 3D model analysis of blade from selected airfoil cross section, with and without winglet is carried out using ANSYS Fluent and the aerodynamic performance is compared to study the effectiveness of the winglet. A comparison of aerodynamic performance of different airfoil geometries is done to find a suitable airfoil shape based on L/D characteristics.
AIRFOIL DIAGRAM SERIES
The selection of different airfoil shapes from NACA series was done and blade aerodynamics was simulated to investigate the flow structures and general aerodynamic coefficients are extracted using ANSYS software. A horizontal axis wind turbine (HWAT) with winglets is proposed. The winglet helps to reduce the induced drag. This study aims to find the changes in the power generation by wind mills after the addition of winglet to wind turbine blade and also to find an optimum ratio between the span of wing and winglet. Induced drag developed by tip vortices stands as a major reason for low power output. Even if power is generated, companies do not find it profitable to sell to the grid. Many stations have little wind to run their windmills. But the wind flow patterns and the nature of the terrain are not always support to the installation of wind farms.
The government offers SOP to private investors to setup wind farms. Government wanted to make India a leading wind power nation.
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