Browsing by Author "Jinadu Abdulbaqi"

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    Aerodynamic lift coefficient prediction of supercritical airfoils at transonic flow regime using convolutional neural networks (CNNs) and multi-layer perceptions (MLPs)
    (Al-Qadisiyah Journal for Engineering Sciences, 2023-05-18) Olayemi Adebayo Olalekan; Salako Isaac Oluwadolapo; Jinadu Abdulbaqi; Obalalu Martins Adebowale; Anyaegbuna Elochukwu Benjamin
    Designing an aircraft involves a lot of stages, however, airfoil selection remains one of the most crucial aspects of the design process. The type of airfoil chosen determines the lift on the aircraft wing and the drag on the aircraft fuselage. When a potential airfoil is identified, one of the first steps in deciding its optimality for the aircraft design requirements is to obtain its aerodynamic lift and drag coefficients. In the early stages of trying to select a candidate airfoil, which a whole part of the design process rests on, the conventional method for acquiring the aerodynamic coefficients is through Computational Fluid Dynamics Simulations (CFDs). However, CFD simulation is usually a computationally expensive, memory-demanding, and timeconsuming iterative process; to circumvent this challenge, a data-driven model is proposed for the prediction of the lift coefficient of an airfoil in a transonic flow regime. Convolutional Neural Networks (CNNs) and Multi-Layer Perceptrons (MLPs) were used to develop a suitable model which can learn a set of usable patterns from an aerodynamic data corpus for the prediction of the lift coefficients of airfoils. Findings from the training revealed that the models (MLPs and CNNs) were able to accurately predict the lift coefficients of the airfoil.
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    Analysis of Flow Characteristics Around an Inclined NACA 0012 Airfoil Using Various Turbulence Models
    (IOP Publishing, 2021-04-21) Olayemi Adebayo Olalekan; Ogunwoye V. O.; Olabemiwo J. T.; Jinadu Abdulbaqi; Odetunde Christopher
    The current paper presents a computational fluid dynamic analyses of the flow characteristics over an inclined NACA 0012 airfoil using various turbulence models at Mach number of 0.13. The primitive continuity and momentum equations were solved using Ansys-Fluent in turn along with Spalart-Allmaras, Realizable k – ε, and k – M shear stress transport. The response of pressure and velocity contours, lift coefficient (Cl) and drag coefficient (Cd) to inclination angle variation from – 14° to 20° are reported. Also, the values of Cl and Cd obtained from the current work were juxtaposed with the equivalent values of experimental data gotten from earlier work done by Abbott and Von Doenhoff and the comparison showed good agreement. Furthermore, the results revealed that stalling occurred between 14° and 16°.
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    CFD Analysis of A 3-Bladed NACA 0018 Vertical Axis Wind Turbine for Deployment in Ilorin, Kwara State, Nigeria
    (FETiCON, 2023-06-05) Olayemi Adebayo Olalekan; Ajide Favour Tomisin; Ibitoye Emmanuel Segun; Obalalu Martins Adebowale; Jinadu Abdulbaqi; Anyaegbuna Elochukwu Benjamin
    During the last few years, vertical axis wind tubines have evolved as a suitable supplement to energy production worldwide. There has been a lot of interest in vertical axis wind turbines as a small-scale renewable power converter because they can be used in places where the wind speeds are turbulent or unsteady. When investigating the aerodynamic characteristics of vertical axis wind turbines, computational fluid dynamics has been shown to be one of the most effective methods. There is a need for better knowledge of the factors that influence the accuracy of computational fluid dynamics. The aim of this paper is to demonstrate the influence of these factors on the simulation of a low-speed turbine to guide the execution of accurate computational fluid dynamics simulations of vertical axis wind turbines at varying tip speed ratios and solidities. To simulate the turbulent, unstable fluid flow around the turbine, we used a 2D SIMPLE approach with the help of ANSYS FLUENT. In the study, it was found that when the tip speed ratio is low, the result is largely dependent on the azimuthal increment, and a fine azimuthal increment of 0.1 is usually better for low tip speed ratios
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    CFD Analysis of a 3-bladed NACA 0018 Vertical Axis Wind Turbine for Deployment in Ilorin, Kwara State, Nigeria.
    (FETiCON, 2023-06-05) Olayemi O. A.; Ajide T. F.; Obalalu A. M.; Ibitoye S. E.; Jinadu Abdulbaqi; Anyaegbun B. E.
    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.
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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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    Characterization of Boeing 777 Nose Landing Gear to Better Withstand Rough Landing
    (Trans Tech Publications Ltd, Switzerland, 2023-09-12) Jinadu Abdulbaqi; Tijani Quadri; Olayemi Olalekan Adebayo; Salaudeen Abdulwasiu
    An important role a landing gear plays is that it aids in the landing and takeoff of aircraft. The landing gear must be designed in such a way that it can take these stresses in static and dynamic situations. This is to accommodate both rough and smooth landings that result from various loads acting upon it, such as drag force, vertical load, and side load. In the aviation industry, landing gear stress is a key concern, and different research in this field has previously yielded excellent results. However, the time has come to raise the bar even higher. This research will focus on the improvement of the Boeing 777's nose landing gear to better withstand rough landings. During the timeframe of this research, motion study in SOLIDWORKS 2020 (Stand-alone license) was utilized to model and analyze various components of the landing gear. The results summarize that a single material should be avoided throughout the components of the landing gear. Components such as pistons with a larger stress allocation should be made of titanium alloy, while components with a lesser stress allocation should be made from aluminum alloy.
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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.
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    Computational Fluid Dynamics Analysis of Mixed Convection Heat Transfer and Fluid Flow in a Liddriven Square Cavity Subjected to Different Heating Conditions
    (IOP Publishing, 2021-04-20) Olayemi Adebayo Olalekan; Khaled Al-Farhany; Olaogun O.; Ibiwoye M.O.; Medupin R. O.; Jinadu Abdulbaqi
    The present study investigates mixed convective and fluid flow characteristics in a lid-driven enclosure filled with air and its walls subjected to various heating conditions. The vertical (left and right) walls of the enclosure are cooled (Tc), and the bottom wall is heated to (Th) while the horizontal lid-driven upper wall is subjected to sinusoidal heating. The dimensionless governing equations (continuity, momentum, and energy transport) were implemented in COMSOL Multiphysics 5.4 software. The influences of Grashof number (103 ⩽ Gr ⩽ 105 ) and Reynold number in the interval of 1 ⩽ Re ⩽ 100 on the average Nusselt number ( NU ) for all walls of the cavity was examined. Furthermore, the results presented in the form of isotherms, streamlines, and the local and average Nusselt numbers in the enclosure for Re ⩽ 100 and Gr in the range of 103 ⩽ Gr ⩽ 105. The results indicated the highest and lowest average rate of heat transfer at the bottom and top walls of the cavity respectively. The top wall region presented a higher velocity as confirmed by the velocity contour plots.
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    Improved Criterion in Method of Assessment of the Safety Level of the Process of Land Recultivation of Places of Ammunition Disposal and Destruction
    (Scientific and Technical Journal, 2022-11-25) Andronov Volodymyr; Didovets Yurij; Koloskova Hanna; Jinadu Abdulbaqi; Koloskov Volodymyr
    The relevance of the research and the need to develop methods that allow assessing the level of safety of the disposal and destruction of ammunition sites are shown not only at the present time, but also in the future when land reclamation measures are applied. An improved criterion for assessing the safety level of the reclamation process of the lands of the disposal and destruction of ammunition sites was developed based on the use of a regulatory approach, and significant indicators were determined, namely: the probability of an explosion, the amount of excessive pressure in the air shock wave, and the level of degradation of the lands of the disposal and destruction of ammunition sites. An improved method of assessing the safety level of the process of land reclamation of the disposal and destruction of munitions by using an improved criterion for assessing the safety level of the process has been developed. The proposed method is suitable not only for long-term evaluation, but also for operational safety management of similar objects. The main advantage of the proposed method in comparison with those used today is to take into account the entire complex of active factors of explosion risk and environmental danger, while minimizing the number of significant environmental quality indicators. Thanks to this, it becomes possible to reduce the amount of calculations required for accurate assessment by a set of regulatory criteria, and also simplifies the assessment procedure without loss of accuracy.
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    Investigation of the Influence of Geometrical Parameters on The Take-off Mass of Unmanned Aircraft Wing
    (АКТУАЛЬНІ ПИТАННЯ СУЧАСНОЇ НАУКИ. ІІ МІЖНАРОДНА НАУКОВО-ПРАКТИЧНА КОНФЕРЕНЦІЯ, 2014-10-24) Jinadu Abdulbaqi; Tiniakov Dmytro; Koloskov Volodymyr
    The aim for carrying out investigation on the wing parameters of an unmanned aircraft take-off mass is to look for its geometrical and structural weakness so as to be able calculate and deduce new parameters that will increase the general performance of the aircraft, thus reducing its take-off mass. These parameters include the relative airfoil thickness, aspect ratio, taper ratio and sweep angle. Along the line in the research, limits are used to define load factor and landing speed. These limits are used, as when displayed on the graph, give the ability to determine the minimal mass within the limit range.
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    Investigation of the Influence of Unmanned Aircraft Takeoff Mass on its In-flight Safety
    (ДЕРЖАВНА СЛУЖБА УКРАЇНИ З НАДЗВИЧАЙНИХ СИТУАЦІЙ НАЦІОНАЛЬНИЙ УНІВЕРСИТЕТ ЦИВІЛЬНОГО ЗАХИСТУ УКРАЇНИ «ПРИКЛАДНІ АСПЕКТИ ТЕХНОГЕННО-ЕКОЛОГІЧНОЇ БЕЗПЕКИ», 2016-12-04) Jinadu Abdulbaqi
    Provision of the in-flight safety for unmanned aircraft vehicles (UAV) brings down the danger of injures for people and material losses in the case of the air-crash involving an unmanned aerial vehicle falling to the ground. One of the important factors ensuring decrease of the catastrophe risk is provision of the strength of UAV carrying structures which may be achieved with decrease of its takeoff mass value.
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    Liquid Nitrogen Injection into Aviation Fuel to Reduce its Flammability and Post-Impact Fire Effects
    (Vilnius Tech, 2023-01-25) Jinadu Abdulbaqi 1*,; Jinadu Abdulbaqi; Olayemi Adebayo Olalekan; Koloskov Volodymyr; Akangbe Ayodeji; Tiniakov Dmytro
    The finite volume method was used to study the characteristic of contaminated aviation fuel with the aim of reducing its flammability and post-impact fire. The flammability levels between pure Jet A-1 and contaminated Jet A-1 are compared using their flashpoints and fire points before and after the introduction of Liquid Nitrogen. Upon heating different mixing ratios (4:1, 3:1, and 2:1), results are analyzed to identify the best volume ratio exhibiting the highest reduction in flammability. Analysis shows that the mixing ratio of 2:1 not only froze but increased the flashpoint of the mixture from (48 ˚C–50 ˚C) to 64 ˚C. For the mixing ratio of 3:1, there was a rise in flashpoint to about 56 ˚C and partial freezing was seen at the topmost surface. At a mixing ratio of 4:1, it was observed that the effect of liquid nitrogen on Jet A-1 was minimal leading to a slight rise in its flash point (50 ˚C). Thus, liquid Nitrogen had a substantial effect on the flammability and flash point of Jet A-1 when mixed in the ratio (2:1) with a freezing time of 30 seconds and an unfreezing time of 17.5 minutes. Hence, Liquid Nitrogen can be used for the flammability reduction of Jet A-1.
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    Model of Safety Management System of Land Recultivation of Places of Ammunition Disposal and Destruction
    (Scientific and Technical Journal,, 2021-11-25) Didovets Yurij; Koloskov Volodymyr; Koloskova Hanna; Jinadu Abdulbaqi
    An analysis of the impact of explosion hazards on the level of environmental safety of disposal and destruction of ammunition. An analysis of existing technologies of land reclamation that can be used for places of disposal and destruction of ammunition, and identified opportunities and limitations of their use. For the first time, a simulation model of the safety management system for land reclamation and ammunition destruction was created. During the development of the model, it is proposed to consider the parameters of the site of disposal and destruction of ammunition, which determine the parameters of explosion risk, and environmental quality indicators, as responses to the influence of factors of operation of the site of disposal and destruction of ammunition. Safety criteria are determined using a regulatory approach in three areas: current factors, explosion risk parameters and environmental quality indicators. The integrated safety criterion is defined as the highest value of all individual safety criteria.
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    Optimization of Aircraft Fuel Dump Rate towards the Mitigation of Post-Impact Fire
    (Defect and Diffusion Forum1662, 2023-06-06) Jinadu Abdulbaqi; Olayemi Adebayo Olalekan; Daniel Joshua; Odenibi John Oluwatomiwa; Tiniakov Dmytro; Koloskov Volodymyr
    This study seeks to improve the utilization of compressed air towards a faster fuel jettisoning, to increase the survival rate of passengers in the event of an accident or aborted takeoffs by augmenting the already existing means of dumping fuel with no considerable increase in overall weight. The aircraft fuel dump sub-system was isolated, this process was achieved with the aid of the venturi effect. A jet which provides a direct connection between the fuel tank and the mixing chamber sucks fuel from the tank, where bypassed air from the compressor expels the sucked air in fine particles. After running the simulation, the mass flow rate was computed. The compressed air inlet has a mass flow rate of 58.5193(Kg/S), the kerosene inlet 1.2385(Kg/S) while the outlet has a relative value of-59.6541(Kg/S).This study seeks to improve the utilization of compressed air towards a faster fuel jettisoning, to increase the survival rate of passengers in the event of an accident or aborted takeoffs by augmenting the already existing means of dumping fuel with no considerable increase in overall weight. The aircraft fuel dump sub-system was isolated, this process was achieved with the aid of the venturi effect. The engine compressor marks the start of the aircraft fuel dump sub-system while an exterior nozzle for displacing the fuel marks its end. This system achieved jettisoning through bled-off air from the compressor, passing through a converging-diverging nozzle (primary supersonic nozzle), thereby creating a vacuum in the mixing chamber. A jet that provides a direct connection between the fuel tank and the mixing chamber sucks fuel from the tank, where bypassed air from the compressor expels the sucked air in fine particles. After running the simulation, the mass flow rate was computed. The compressed air inlet has a mass flow rate of 58.5193(Kg/s), and the kerosene inlet 1.2385(kg/s) while the outlet has a relative value of -59.6541(kg/s).
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    Parametric studies of mixed convective fluid flow around cylinders of different cross‐sections
    (Wiley, 2023-05-22) Olayemi Adebayo Olalekan; Ibitoye Emmanuel Segun; Obalalu Adebowale Martins; Al-Farhany Khaled; Jolayemi Samsudeen Temidayo; Jinadu Abdulbaqi; Ajide Favour Tomisin; Adegun Kayode Isaac
    A numerical study of mixed convective heat transfer in a lid‐driven square enclosure containing a hot elliptic cylinder is conducted. The impacts of the Grashof number (103 ≤ Gr ≤ 106), Reynolds number (1.0 ≤ Re ≤100), cylinder tilt angle (0° ≤ ϕ ≤ 90°), and aspect ratio (1.0 ≤ AR ≤ 3.0) have been examined for a fluid of Pr of 0.71. The horizontal enclosure walls are insulated, while its vertical walls are restricted to a nonvarying temperature Tc, whereas a sinusoidal temperature of Th + ∆T sin(πxL/ ) is imposed on the wall of the elliptical cylinder. The governing equations are solved using COMSOL Multiphysics 5.6 software. The fluid dynamic and the heat transport profiles between the enclosure and the elliptical cylinder walls are represented by the stream function, isothermal contours, and average Nusselt number. Results estab­lished that for all the considered aspect ratios, the thermal heating range of 103 ≤ Gr ≤ 104 is predomi­nantly a conduction mechanism. The critical position of the ellipse where the inclination effect becomes insignificant is determined by the Grashof number and aspect ratio when the Re = 100. The strength of vortices and cell numbers are significantly influenced by the aspect ratio, particularly when the Gr =104 . When AR =1.0, the average heat transfer from the cylinder remains the same regardless of the cylinder's orienta­tion. The impact of cylinder orientation on heat transfer from the cylinder wall is minimal for 1.5 ≤ AR ≤ 2.0. For AR values of 2.5 ≤ AR ≤ 3.0, increasing the inclination angle does not result in improved heat transfer. The influence of the increasing inclination angle on the right wall diminishes as the angle increases, except when the Grashof number is greater than 105, where the rate of heat transfer is enhanced for inclination angles beyond 45°.
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    Unveiling the Future: A Survey of Electric Propulsion Systems and their Pivotal Role in Shaping the Next Frontier of Space Exploration
    (Science Publications, 2024-01-04) Jinadu Abdulbaqi; Okikijesu Omolona Olajide; Akangbe Tunde Ayodeji
    Electric propulsion represents the future of space travel, which is a promising technology for Earth-orbital and deep space missions, including potential applications in human Mars missions. The past decade has witnessed substantial progress in the conceptualization and experimentation of electric thrusters and their propellants, signaling a transformative era in space exploration. This review provides an overview of the comparison between electric and chemical propulsion, followed by a detailed examination of current research and development on various types of electric propulsion thrusters. The discussion encompasses the adoption of diverse technologies to enhance the scalability of these thrusters, presenting a comprehensive outlook on the future of space exploration.