![]() Various members of the NACA 4-digit airfoil family and other synthetic geometrical shapes are examined in this work. ![]() The commercial expert FLUENT is applied for the computational process to simulate the aerodynamic characteristics of airfoil section in ground condition. The numerical modeling and its grid are generated using the software GAMBIT. Parameters affecting aerodynamic efficiency of WIG wing are investigated in ground condition by computational fluid dynamic codes. In the present work, improving the efficiency of WIG craft is discussed throughout modifying the design of wing section. There are still many aspects of ground effect that need clarification when selecting airfoil section in ground. These craft were designed for operation in open air rather than close to a ground plane. Early WIG craft used classic wing sections such as the NACA series. Selecting or design of airfoil section is one of the most basic decisions to make in the design of a wing of WIG craft and consequently, the overall efficiency. This is due to the lack of information about its performance data and the coupled relation between hydrodynamic and aerodynamic force effects on this craft. Improving the efficiency of wing-in-ground (WIG) marine craft is challenging. Keywords: Aerofoil, NACA, Flaps, Wind Tunnel Testing, Composite material. So we make use of the composite material carbon-carbon to replace the wing material for the aircraft. Composite materials are the most advanced materials which have a longer life and performance characteristics than other materials. The NACA24012 aerofoil series finds application in general aviation, piston powered bombers, transport, commuter and business jets. Two component balances is used to determine the wing parameters. The control surfaces attached with the wing are flaps, trim tabs and they are actuated using servo. This aerofoil has low pitching moment and has little roughness effect. This aerofoil has high coefficient of lift than other airfoils. Cambered wing with NACA24012 aerofoil series has been chosen for the estimation. The main aim of our project is to estimate the wing parameters such as lift, drag, coefficient of lift, coefficient of drag, stall point for varying angle of attack and to visualize the flow using low speed wind tunnel. These values were also compared by running different simulations with change of input parameter i.e. Coefficient of lift and drag were also recorded. While performing the simulations, meshing techniques, pre-processing and post processing sections and evaluation of a simulation are being learnt. The research aims to perform a CFD analysis on an aircraft model using FLUENT solver. It means that the laminar and turbulent flow and several combinations of the angle of attack have been considered. The computations were performed for different angle of attacks. The CFD simulations were performed on the computational model of an airfoil. Further, a way of analysing the results and some of the outputs of the simulations and analysis has been presented. The pre-processing includes the creation and modelling in SOLIDWORKS and modification of the surface mesh in ANSYS. The model was prepared with the software SOLIDWORKS. The fluid flow simulations are obtained with the FLUENT software package of ANSYS. The primary focus is on the simulation of the airflow around the airfoil. This research describes simulation of computational fluid dynamics (CFD) problems that occur in physical practices.
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