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This work evaluates the impacts on the temperature and flow fields caused by alteration on the geometry of an automotive engine cooling water pipe section. The pipe section studied is located after the water pump. The straight pipe section was altered to a curved section and it was located closer to the exhaust pipe, to attend engine downsizing demands. The analysis was carried out though the finite volume method, considering steady-state, bi-dimensional flow. The results point out that pressure drop in the conduit is little altered with geometric variations, but the temperature conditions are affected by the proximity of the duct to the heat source.

The availability of new technologies and the growing interest in the development of autonomous aircraft has created a demand for performance evaluation of aircraft flying at high altitudes over a long period of time for applications such as monitoring, telecommunications, etc. This work presents a study on the use of wings with high aspect ratio for the application in unmanned aircraft, that fly at high altitudes and require great endurance to remain flying as long as possible. With reference to the AeroVironment Helios aircraft, which hit the altitude record in 2001, flying at more than 29,000 meters altitude, a comparison was made between five wings with different wingspan from the aerodynamic and structural point of view. The aerodynamic performance of each wing was calculated and structural design and sizing was performed, assuming that it is the main structural component of the wing.

This paper presents an aerodynamic analysis of a single-seat vehicle designed for the Formula SAE competition. The analysis was conducted using the finite volume method via computational fluid dynamic (CFD) considering a three-dimensional steady-state. In this case, the initial concept and a proposal concept with aerodynamic improvements were evaluated. The proposal consisted in geometric modifications to mitigate the impact caused by the wind along the body in order to minimize the drag coefficient. Based on the aerodynamic study, we were able to create proposals where the drag coefficient could be minimized, because the better understanding of flow's parameters. For each geometric modification the results are shown in order to establish advantages and disadvantages in relation to drag coefficient.