| Summary: | 碩士 === 中華大學 === 機械與航太工程研究所 === 90 === Abstract
The MAV(Micro Aero Vehicle) can be applied for a variety of purposes for example the surveillance and communication for military or the disaster rescuing and environment monitoring for civilian. Due to its small size, light weight and low speed, the external forces are the big factors that can effect MAV’s performance such as Reynold’s number and side-shearing wind. Therefore, the investigation of aerodynamic performance and design/fabrication a MAV are goals in the study. Three phases are discussed. First, the 2D and 3D aerodynamic calculation and flow field simulation of Clark’s Y shape airfoil for a MAV are studied by employing the Star-CD code. This code can investigate the problems when the MAV under a low Aspect-ratio and low Reynold’s number situation. Second, making a chord length 16cm, airfoil span 20cm and total weight 125 gram electric motor plane. The third, using the water tunnel test results to compare with those of numerical analysis. The 2D airfoil numerical results show ±5 degree of angular of attack resulting in re-circulating flow, but 3-D shows the re-circulating flow happening when the angular of attack reach to ±10 degree. If the MAV with vertical rudder, the slope of lift coefficient will become larger. The symmetrical airfoil Clark Y shape has the larger Cl than that of NACA 2415, and uniform surface pressure distribution thus the Clark Y shape wing with better aerodynamic properties and manipulating. The prototype of MAV “Flyer” has been done the flying test, it flies in good shape, stable and it will be improved continuously. Results of water tunnel test are very consistent with those of numerical analysis and the dye-flow visualization show the position of re-circulating flow is located at 2/3 chord length.
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