Research On The Performance Of The Inlet Of Ram Air Turbine And Numerical Simulation Of Aerodynamic Performance Of Wind Turbine Airfoil Profile

Through a numerical simulation of the inlet a ram air turbine, this paper analyzes the inlet's aerodynamic performances under varities of work conditions. After that, according to the calculated results of the general performance, with the priority to make little change to the geometric model, adding a suction boundry layer seam to suppress the flow separation in the flow passage, which can apparently improve the quality of the inlet's aerodynamic performance.The results of the research show that:The inlet can satisfy all the normal requirements from the ram air turbine under all the considered conditions. What's more, through the calculation of the inlet's total aerodynamic performance, it discovered that this particular turn angle gemetric model can cause a serious flow separation in the inner duct, which will have a certain influence to the aerodynamic performance.After the suction boundry layer seam added on the gemetric model, it can suppress the flow separation of the inner duct, thus improve its flow state, and attain the objective to improve the performance of the inlet .The sixth chapter of the paper introduced a numerical simulation of the planar aerofoil. As a kind of renewable energy, with pureness and no pollution, the wind power generation becomes more and more popular in countries all over the world. However, to rise the aerodynamic quality of the aerofoil is an important requirment in order to develop the large aero-generator. So the paper calculated the performance and the flow field of a certain kind of aerofoil with a series of angle of attack, from -2.23°to 90°, simulated with different turbulant models.After the contrast as well as the analysis, it found that: before the flow separation occurred, different turbulent models made little differencs to the results, which are generally consistent with the experimental result. As the angle of attak rise to more or less 12°, the flow separation takes place at the tail part of the aerofoil's suction surface, the bigger angle of attack, the worse flow separation, as the angle increase after reaching 45°, the lift cofficent begins to depress, while the drag cofficent raises apparently. However, the calculated and experimental results don't coincide well, and k-ωLow Re L-S models make a relatively better match to the experimental in the consequence than the Spalart-Allmaras model.