Computational Analysis on Partial Flexible Tubercle Wing

In this paper, NACA 4412 airfoil, NACA 4412 airfoil with partial flexible sheet, NACA 4412 airfoil modified with leading edge tubercle and NACA 4412 airfoil modified with leading edge tubercle with partial flexible sheet. All the above four models have the same span length and span area. The material of wing is Alumina and the material for flexible membrane sheet is Silicon rubber. The models were created in Solid works, and Ansys Fluent Flow Workbench was used for analysis The analysis is done for 4 models with 8 cases of angles of attack 0, 5, 8, 10, 12, 15, 18 and 20 degrees. A total of 32 cases were studied. The majorly studied definitions were pressure contours and velocity contours. Drag and lift values were studied along x and y axis during simulation. These values are then used to view the graph for each modelled case. The graph is drawn for alpha versus coefficient of lift, coefficient of drag and coefficient of lift by drag values. From the results, one can conclude that the proposed model of partial flexible tubercle wing has performed better than the baseline model. © 2023. Carbon Magics Ltd.