Determination Of Stalling Region For Specific Turbine Blade's Profile

Kamaruddin, Muhammad Syahzani (2017) Determination Of Stalling Region For Specific Turbine Blade's Profile. Project Report. UTeM, Melaka, Malaysia. (Submitted)

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Abstract

Stalling is the phenomena that always happened at the blade profile or airfoil. There is some consideration that need to be taken to curb the stalling phenomena happened to the blade profile such as the blade profile shape, the inlet velocity, and the angle of attack (AOA) for the blade profile. Stalling happened when there is a separation flow at the upper chamber and lower chamber of the blade profile. The separation flow will produce a turbulence flow when it passed the trailing edge of the blade profile. When the region of turbulence flow become larger, the lift coefficient starts to decrease thus, the blade profile had faced the stalling phenomena. The main objective for this study is to find the stalling region for NACA 8415 blade profile at the various angle of attack. This study used computational fluids dynamics (CFD) approach to determine the stalling region. The software that had been used to make the computational fluids dynamics simulation is ANSYS fluent 17.1 version. The analysis for this study only focusing on 2-dimensional analysis geometry only. The fluid is hot air and the inlet velocity is 680m/s at 500°C. The coefficient of lift and drag had been obtained from the CFD simulation and the coefficient of lift and drag vs angle of attack (AOA) had been plotted. From the finding it had been found that the coefficient of lift starts to decrease at the angle of 15°. Thus, the stalling region will be started at angle of 15°.

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