Evaluation Of The Mechanisms For Inducing Leading Edge Vortex Using Ansys Fluent
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Date
2021-06-01
Authors
Idris, Mohamed Nizam Mohamed
Journal Title
Journal ISSN
Volume Title
Publisher
Universiti Sains Malaysia
Abstract
This thesis evaluates the mechanism for inducing leading edge vortex using synthetic jet utilising ansys fluent on an airfoil due to aerodynamic in the transitional Reynolds number regime. Two-dimensional simulations based on the concept of fluid-structure interaction at low-to-moderate Reynold’s number (6.77𝑋104≤ Re ≤ 6.77𝑋105) are carried out on a NACA 4412 airfoil with several angles of attack using Ansys Fluent. The model of simulation that being used is the laminar flow around the airfoil. To compute the flow response of the jet synthetic from the airfoil, a graph of velocity was constructed through the simulation process to ensure that the flow on top of the jet synthetic is precise. The process of releasing the air periodically through the pore/orifice was created by adding data files through the transient table file. The simulation was simulated at different airspeeds ranging from 1 m/s to 10 m/s. The fluctuation of lift and drag coefficient was increase as the jet velocity is increase. The angle of attack of the airfoil also holds a huge role on the fluctuation effects of lift and drag coefficient. The point of separation of flow on the surface of the airfoil is found to be affected by then angle of attack and jet output speed. The wake of the airfoil at the trailing edge also can be observed to be affected by the jet output is eject through the orifice. As a result form this study, 10 m/s jet could enhance the lift and drag coefficient, but it has a major drawback. So, the optimised solution with the most enhance aerodynamic properties and minimised drawback is to use jet 10 m/s at 6º.