Setyo Hariyadi Suranto Putro(1), Sutardi Sutardi(2). The thickness of the airfoil is a very important design parameter and as always expressed as a percentage of the total chord. This often varies down the span of the wing as the wing tapers from the root to the tip. Early take-off from water with about 10 knots (20 %) and decrease in power required to come over take-off resistance with about (30%) is recorded when the classic NACA section is replaced with new airfoil section. Comparative Study Aerodynamics Effects of Wingtip Fence Winglet on Fix Wing Airfoil Eppler E562. The length of the airfoil from leading to trailing edge is known as the airfoil chord. The proposed mathematical model is developed to examine the new airfoil sections as an illustrative application. An iterative computer program is structured using FORTRAN language. A mathematical model to represent the power prediction for WIG craft is developed, including a detailed analysis of the aerodynamic and hydrodynamic forces acting on the vehicle, and the effect of ground proximity. The proposed airfoil is compared with the classic airfoil NACA 4412. New airfoil section shape, suitable to operate efficiently in ground regime is designed different from classic airfoils shape. The influences of changing airfoil shape parameters such as, camber, maximum thickness and its location, angle of attack, velocity, and ground clearance on the aerodynamic efficiency are considered in ground condition. 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 shape of the NACA airfoils is described using a series of digits following the word 'NACA'. Last two digits describing maximum thickness of the airfoil as percent of the chord. Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord. The numerical modeling and its grid are generated using the software GAMBIT. The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The NACA four-digit wing sections define the profile by: First digit describing maximum camber as percentage of the chord. 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.
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