# Introduction n airfoil is the shape of a wing or blade (of a propeller, rotor or turbine) as seen in crosssection. The design and analysis of the wings of aircraft is one of the principal applications of the science of aerodynamics, which is a branch of fluid mechanics. Little modification in the airfoil has a direct impact on the performance of an aircraft. Here, we design a 3D air wing and solve the flow equations in a CFD solver and study the characteristics features of the flow around a finite wing and the effect of the tip vortices that are caused by the difference of pressures between the lower and upper portion around the tips on an air airfoil. Better visualization of this vortex flow past an aircraft helps in optimizing the design of a wing. # II. # Disturbance of Flow Past Airfoil # Design, Data Generation and Visualization Some of the important works done on Airfoils have been studied before solving this problem. This paper serves as a basis for understanding, designing and solving the flow problem. A detail of the literature survey done has been included in the references list. The Ansys workbench has a comprehensive list of software for doing various Structural and Fluid analysis and is also equipped with superior visualization capabilities which are in par with any other dedicated visualization software's. This workbench has been used for designing, solving and visualizing the results. Execution of the Project: The project is executed in three phases. A medium size mesh is used for meshing purpose. A refinement of the mesh is done near the wing region as it is the focus of our interest. From the data that is generated, the flow is visualized using various visualization tools like contours, vector visualizations, particle tracing etc. IV. Although the Light Jet Executive has been successfully modeled and meshed, there has been certain constraints due to which it could not be solved. Some of the major limitation were the problem with integrating the mesh of the far field with the Light Jet Executive. # Results Initial attempts to make the mesh very coarse were successful however solving the problem gave totally unrealistic results and was not stable. V. # Conclusions and Future Work ? The air wing and domain is modeled, meshed and solved and various post processing visualization options has been used for better understanding & investigation of the flow. ? Visualization options such as slicing and volume rendering proved extremely useful for doing the investigation of flow pattern. ? A better refinement of the mesh and boundary mesh and implementing better solvers can give accurate results for the 3D wing which can be potentially be validated with experimental results. ? An adaptive mesh refinement near the high gradients especially close to the wing gives more accurate results. ? Refinement of mesh and better meshing options required for solving Light Jet Executive Model. 1![Figure 1 : Cross-section of a wing](image-2.png "Figure 1 :") 2![Figure 2 : Visualization of vortex flow past an aircraft](image-3.png "Figure 2 :") 3![Figure 3 : Disturbances created on an aircraft A lot of disturbance is created in the air when an aeroplane flies. It is through the study of these disturbances of the flow past the airfoil, lots of design considerations are done. Performance of the aeroplane is directly related to the size & shape of airfoil. A considerable difference is seen between the airfoil of the commercial airlines and the defense plane as most of the time better optimized airfoil leads to bad fuel consumption because of the huge drag and vice versa.](image-4.png "Figure 3 :") ![Pre-processing o Design of the model is done using Sumo-2.4.1 and Design Modeler o Meshing the model in Ansys workbench ? Solving o Solving using CFD package Ansys Fluent ? Post-Processing o Analyzing the results using various visualizations o Interpreting the results a) Pre-ProcessingThe design of the air wing is done using SUMO 2.4.1 and the wing is imported into Design Modeler to create far field.](image-5.png "?") 4![Figure 4 : CAD model of the 3d Air wing with the far field-](image-6.png "Figure 4 :") 5![Figure 5 : Mesh of the entire domain](image-7.png "Figure 5 :") 68![Figure 6 : Static Pressure and Relative Pressure Contour of the entire domain From the above visualization, we cannot make any worthwhile inferences or analysis. This is a crude data result and we need more refine visualization techniques. a) Slicing of the Pressure Contour](image-8.png "Figure 6 :Figure 8 :") 11![Figure 11 : Recirculation of the flow-XY Plane From the above Vector visualization in XY plane we observe the recirculation of the flow at the trailing end of the airfoil. At small angles of attack, air flows smoothly around an airfoil providing lifting force through the difference in pressure across the top and bottom of the airfoil. As the angle of attack increases, the lift produced by the airfoil increases as well but only to a point.](image-9.png "Figure 11 :") 12![Figure 12 : Vector of the Pressure contour in XZ Plane](image-10.png "Figure 12 :") 14![Figure 14 : Vector of the pressure contour of the 3d wing in Isometric view. From the above figure we can clearly see that there are tip vortices which influence the drag of the airfoil c) Other Display Options Used In Visualization Listed below are some of the other visualization tools used in post-processing phase.](image-11.png "Figure 14 :") 15![Figure 15 : 3D Wing Mesh in Ansys Fluent](image-12.png "Figure 15 :") 17![Figure 17 : 3D Wing vector of static pressure-Cone Options](image-13.png "Figure 17 :") 20![Figure 20 : Light Jet Executive CAD Model](image-14.png "Figure 20 :") ![](image-15.png "") ![](image-16.png "") ![](image-17.png "") © 2014 Global Journals Inc. (US) * Stability derivatives of Cessna aircraft ]LCessna Leisher Cessna Aircraft company 1957 * Tornado, a vortex lattice MATLAB implementation for Linear Aerodynamic Wing applications Melin December 2000 Sweden Royal Institute of Technology (KTH Masters thesis * Computational Fluid Dynamics JMoran 1984 Weily & Sons * A critical assessment of wind tunnel results for the NACA 0012 Airfoil WJMccroskey AMES Research centre * Lessons from LESFOIL Project on Large Eddy Simulation of Flow around an Airfoil ChristopherPMellen University of Karlsruhe * Numerical Simulation of the Dynamic Stall of a NACA 0012 Airfoil using DES and Advanced OES/URANS Modelling GMartinat