DSGN313 – Coursework A – CFD Assignment This 7 credit coursework should be carried out individually. The deadline for this coursework is 23.59 on 4th November 2011.You must submit your coursework electronically via the SCOLAR system accessed from the DSGN313 Portal site…
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Please note that the University enforces a penalty of zero percent for work submitted after the published deadline without valid extenuating circumstances (see University student handbook on the portal for details). Intended outcomes – By the end of this coursework, you should be able to: Carry out a CFD simulation using ANSYS Workbench/CFX, demonstrating ability to import geometry, produce a mesh, set up and solve a simulation and effectively post-process results. Evaluate grid-dependency of a solution and demonstrate the process of finding a grid-independent solution. Demonstrate ability to compare CFD results with published experimental data, and critically evaluate results with reference to relevant literature. Recognise capabilities and limitations of a CFD analysis in a particular application. Present results of a CFD analysis clearly and concisely, with appropriate output from CFD-Post. Aim To use ANSYS CFX to simulate the flow around a two-dimensional NACA 642-015 aerofoil section at a 5o angle of attack and to assess the accuracy of the simulation. Problem specification It is important to understand the lift and drag characteristics of aerofoil sections when designing devices such as aircraft (wings and tails) or yachts (rudders and keels). Traditionally, foil theory has been used to give performance estimates, along with extensive experimental testing. More recently, CFD has become another possible option when investigating foil performance. In reality, foils exhibit three-dimensional performance, because flow around the tip of the foil affects lift and drag. However, it is useful to determine performance of a two-dimensional foil – that is one that is so long (approaching infinite length) that the effects of flow around the tip are negligible. You are going to use CFD to simulate a 2-d foil, and compare your results to those obtained experimentally in a wind tunnel, detailed in a NACA paper from 1945. Instructions You will not be writing a formal report for this project. Instead, you will work through this document (using it as a template), adding content and answering questions as instructed. You will then submit the completed document for assessment. Note that answers/images, etc. do not have to fit into the space provided – insert extra space as necessary, but keep answers concise. Carry out the steps as follows: Carry out a basic CFD simulation (named “Run_1”) of a NACA 642-015 foil noting the following: The foil geometry has been created in SolidWorks for you – the file aerofoil_CW_2011.SLDPRT can be found on the DSGN313 Tulip site under CFD Coursework. The file Aerofoil_Instructions_2011.doc (also on the portal) explains how to modify the geometry parameters using SolidWorks. Note that it is down to you to modify dimensions to set the extents of your domain in all directions, and to set your foil chord and angle of attack – don’t just run with the dimensions given to you. Your simulation should be for a 5o angle of attack, and a 24 inch chord length (for comparison against the NACA experimental data). You should run your simulation at a Reynolds number of 6x106. Note that the length scale used in the Reynolds number is the chord length of the airfoil section in the model. Use ‘Water’ as the fluid and assume that the flow is incompressible, steady, isothermal and turbulent. Use the k-? turbulence model. Run_1 should be a coarse, unrefined mesh purely to get your simulation working (you
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