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Master Thesis Report Conclusion and Recommendation position. As a result of the change in inlet incidence angle, a shift in the position of the shockwaves as well as slight difference in the wake pattern was expected. Close to the tip location, the pressure rise is reduced as compared to the original case as a result of the reduced inlet total pressure. As for the hub region, the pressure rise is larger as compared to the original case as a result of the increased inlet total pressure. It is also noted that the shock shifts forward in the case of the reduced total pressure as a result of the increased incidence angle and vice versa. For the comparison of the 3D results between the case of a rotor with and without casing under uniform inflow condition, it was found that the case of the rotor without the casing exhibits a reduc- tion in isentropic efficiency. This is mainly because of the increased tip leakage losses as compared to the case of a rotor with casing. However, it is noted that the pressure ratio over the unducted rotor is slightly higher as compared to the ducted rotor. In this simulation, the total duct length is relatively short and therefore the pressure induced by the shroud does not significantly add to the total pressure ratio. The results of the 2D simulation showed that the BSpline surface generation algorithm gives a bet- ter fit closer to the tip section as compared to the hub section. Therefore, a more accurate surface generation algorithm was needed. At the point of writing this report, a new algorithm was already implemented in the later version of the Blade Modeller. The main goal of this new algorithm was to ensure that the generated surface fits through the control points of all the control profiles. Secondly, it was found that the accuracy of the 2d fitted profiles are very sensitive to the actual location of the leading and trailing edge. Therefore, an accurate manual adjustment of the actual LE/TE position from the closest selected distributed point is required at the early stage of the fitting process. Finally, the analysis made from the 3D simulation showed that the blade profile can be better shaped to improve the performances under non uniform inflow condition. Although it is difficult to quan- tify the actual change in the blade angle at this stage of the research, some possible direction of investigation will be discussed. As a result of the change in inlet total pressure and consequently an increase/decrease in the inlet incidence angle, adjustment to the blade profile can be made in term of the inlet incidence angle or the stagger angle. It is noted that changing the inlet blade metal angle influences the enthalpy/pressure change across the blade profile and consequently the thermodynamic properties of the engine cycle. Therefore, it is not recommended to change it if possible. Implement- ing changes to the stagger angle at certain span position is a possibility. Detailed investigation by numerical optimization is necessary in order to find the optimal stagger angle at each span position.PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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