This project, we are considering low speed air flow over the NACA 0012 airfoil at an angle of 2o And the lift force is the force that helps the airfoil to gain altitude. Drag force is a mechanical force generated by the airfoil These flow there are forces developed that are normal and parallel to the flow, and these forcesĪre called drag force and lift force. It is a kind of flow that flows over the outside theīody of an object in our case ‘the airfoil.’ These fluid flow moves around the airfoil. The flow over the airfoil is an external flow. 23Ģ° Attack angle and 15,000 mesh element.23Ģ° Attack angle and 40,000 mesh element.23ġ4° Attack angle and 15,000 mesh element.24ġ4° Attack angle and 40,000 mesh element.24 20Ģ° Attack angle and 15,000 mesh element.20Ģ° Attack angle and 40,000 mesh element.21ġ4° Attack angle and 15,000 mesh element.22ġ4° Attack angle and 40,000 mesh element.22Ĭoefficient of drag 𝐶 𝑑 and coefficient of lift 𝐶𝑙. Stream line.17Ģ° Attack angle and 14,000 mesh element.17Ģ° Attack angle and 40,000 mesh element.18ġ4° Attack angle and 15,000 mesh element.18ġ4° Attack angle and 40,000 mesh element.19Ĭonvergence. Static Pressure.15Ģ° Attack angle and 15,000 mesh element.15Ģ° Attack angle and 40,000 mesh element.16ġ4° Attack angle and 15,000 mesh element.16ġ4° Attack angle and 40,000 mesh element.17 14Ģ° Attack angle and 15,000 mesh element.14Ģ° Attack angle and 40,000 mesh element.14ġ4° Attack angle and 15,000 mesh element.15 Velocity Vector.12Ģ° Attack angle and 15,000 mesh element.12Ģ° Attack angle and 40,000 mesh element.12ġ4° Attack angle and 15,000 mesh element.13ġ4° Attack angle and 40,000 mesh element.13 Pressure Coefficient.10Ģ° Attack angle and 15,000 mesh element.10Ģ° Attack angle and 40,000 mesh element.10ġ4° Attack angle and 15,000 mesh element.11Īttack angle with 40000 mesh element. 8Ĭomparison of Coefficient of Pressure at 14o 7Ĭomparison of Coefficient of Pressure at 2oĪttack angle with 15,000 & 40,000 mesh element. 6Īttack angle with 15000 mesh element.7Īttack angle with 40000 mesh element. 6Ģ° attack angle with 40000 mesh element. 5Ĭoefficient of Pressure.6Ģ° attack angle with 15000 mesh element. 4īoundary Value Problem.4īoundary Conditions. Mesh element or the attack angle increases.Ībstract.1 Lift and drag coefficient increases as the number of Independence was achieved for 2° attack angle, for 14° attack angle which is more than the stallĪngle, mesh independence was not achieved.
Procedures were done by following the steps provided Cornel University website. The flow was modeled as incompressible and inviscid. The Reynolds number based on the chord is The given inlet velocity of 0.25 m/s, was modeled and computational fluid dynamic (CFD)Īnalysis were performed using FLUENT in ANSYS.
In this report, a low-speed airfoil over the NACA 0012 airfoil at 2° and 14° attack angles with
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