Browsing by Author "Olayemi A. Olalekan"

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    CFD analysis of vertical axis wind turbine with modified blades for deployment in Ilorin, Kwara state, Nigeria
    (Al-Qadisiyah Journal for Engineering Sciences, 2024-12-16) Ajide F. Tomisin; Olayemi A. Olalekan; Jinadu Abdulbaqi; Olayemi O. David; Amoloye O. Taofiq; Oladimeji T. Leke; Bambe M. Jumoke
    Researchers and the energy industry are currently focusing their efforts on optimizing the effectiveness of vertical-axis wind turbines (VAWT) to cut down on the reliance on energy supply from fossil fuels which releases gases that are toxic to the environment. As such, several methods have been applied, including increasing the velocity and modification of both the trailing and leading edges of the aerofoil. In the present investigation, numerical studies of the flow on the wind turbine blades with a NACA0015 airfoil section equipped with and without tubercles on the trailing edge were conducted using ANSYS Fluent. A computational domain of 2000 mm by 35000 mm was employed with the K-W SST turbulence model. This two-dimensional computational fluid dynamics (CFD) analysis was performed with Ilorin, Kwara State, Nigeria wind data that was received from the Nigeria Meteorological Agency (NIMET). The modified blade with a wavelength of 0.09m and an amplitude of 0.004m is seen to have a better thrust than the unmodified blade. It produced a thrust of 118 N for a tip-speed ratio (TSR) of 4.0 compared to 109 N of the unmodified blade at the same TSR and that of the modified blade (1) which attains 107 N. Also, its coefficient of performance is 5% and 6% higher than that of the straight and modified blades (1) respectively, These results suggest that an increase in the tubercle’s wavelength and amplitude increased the maximum thrust.
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    Computational Development and Aerodynamic Analysis of a Single-Stage Launch Vehicle to Subdue Post-Launch Risk
    (FETiCON, 2023-06-05) Jinadu Abdulbaqi; Koloskov V.; Dmytro T.; Oluwatofunmi A. M; Olayemi A. Olalekan
    The aerospace industry has prioritized reducing fatalities and failure rates after the launch of a vehicle resulting from system or engine failure. Rocketry has been difficult over the years, and international players in the industry are constantly attempting to learn from any failures. This paper aims to decrease material, resource, and payload waste while ensuring crew safety by focusing on the computational modelling and aerodynamic analysis of a single-stage launch vehicle. CATIA V5 was utilized to create the computational model of a triggered nose cone rocket booster while ANSYS was used to analyse the trigger nose cone at different angles of attack and determine how the trigger nose cone will behave in case of emergencies such as system or engine failure, which could lead to the complete explosion of the launch vehicle. Based on the current findings, the trigger nose cone is not in the safe zone when ejected at an angle of attack greater than 20° due to the shockwave's effect on its surface when ejected from the main body of the launch vehicle.