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Once the airfoil had been designed a thorough static analysis was made. The analysis gives all the characteristics of the airfoil as well as the forces on the airfoil as it is flying. The analysis is made through the computer program, FLUENT, at the Virginia Tech Research Center. The analysis is made from the loading of the airfoil which determines the forces on the airfoil. After the airfoil was designed the group placed the airfoil into the wing and simulated the lift through FLUENT. The analysis also calculated the values of the wing such as the induced drag and pitching moment. The analysis can give the designer the lowest weight with the best characteristics but is not to be taken literally since there are many other variables that affect the performance of the airfoil such as the type of fluid in the wing.
The design of the wing was important and had many variables that affected the success of the design. Some of these design variables included the size of the wing, the location of the ailerons, the design of the leading edge, the design of the trailing edge, the location of the servos, the location and size of the struts, the location of the airfoil, the size of the horizontal tail and the size of the wing. The groups came up with many different possible solutions to theses variables and choices. The team's conclusions of what was the most efficient and effective were the following, the size of the wing should be about 18 inches wide and 2 feet 7 inches long. The ailerons should be at the wings center of gravity. The struts should be positioned along the rear spar and the servos along the midpoints of the ailerons. The leading edge should be V-shaped in cross section to help with lift. The wings height should be at least as tall as the leading edge to be able to mount the wing to the fuselage.
For the wing shape, the team chose elliptical to provide a high lift to wing ratio, and obtain minimal drag, and rectangular to provide minimal drag. Other than that the team decided to use an elliptical airfoil for both the horizontal and vertical stabilizers because it gives the best performance of the airfoils that were considered. The vertical tail would have a round shape for best performance and minimal weight. The horizontal stabilizer would have an elliptical shape for maximum lift and minimal drag.
Based on the research the group had performed last semester, the use of NACA0012 airfoil for horizontal stabilizer will provide minimum drag and maximum stability since it has a symmetrical shape of top and bottom. Moreover, the use of a thin planar surface for the vertical tail will provide a minimum weight to the plane. The vertical tail will have a round shape in front and flap on the rear side.
The team design and build a new plane that will be created by selecting an appropriate airfoil and creating the wing shape. In step 1 of the project, the team will select an airfoil that will be used on the aircraft and will be created by using ModelFoil software. 827ec27edc