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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.
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.
Kwasu Function: A Closed-Form Analytical Solution to the Complete Three-Dimensional Unsteady Compressible Navier-Stokes Equation
(American Institute of Aeronautics and Astronautics, 2018-01-07) Taofiq O. Amoloye
An attempt is made to re ne the classical potential theory of the flow over a circular cylinder by introducing a viscous sink-source-vortex sheet on the surface of the cylinder. These singularities introduced into the flow are modeled as concentric at every location. The vortices are modeled as variations of Lamb-Oseen, Batchelor and Burgers vortices and analytic expressions for their strengths and those of the sinks/sources are obtained from the classical theory. These are employed to obtain a viscous potential function named the Kwasu function which provides a closed form analytic solution to the complete three dimensional unsteady compressible Navier-Stokes equation. Preliminary results of the work show that the theory presented captures important features of a bluff body flow includin flow separation, wake formation, vortex shedding as well as compressibilty effects. The condition at a viscous wall is shown to be transient from slip towards a complete no-slip for a steady freestream flow. It is the hope that the present theory will shed more light on the important phenomenon of turbulence in planned future work in which quantitative analysis of the theory will be carried out.
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.
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°.
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.
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.
Production of gluconic acid from sweet potato peels using naturally occurring fungi by submerged fermentation
(Journal of Biological Research & Biotechnology, 2023) Ajiboye Adeyinka Elizabeth and Said Rukayat Olaitan
Optimization and Modelling of Bio-Oil Yield from the Pyrolysis of Jatropha Curcas Seed Using Optimal Design and Artificial Neural Networks
(LAUTECH, 2023) Oladosu, K. O.; Amoloye, T. O.; Mustapha, K.; Oderinde, J. O.; Babalola, S.
Better quality and quantity of pyrolysis products from biomass can be obtained by regulating the input parameters of the pyrolysis process. Pyrolysis of Jatropha Curcas seed mixed with alumina catalyst was carried out in a fixed bed reactor to study the effects of temperature, time, and particle size on bio char and bio-oil yield. The bio-oil yields were optimized using the Optimal Design (OD) under the Combined Methodology of the Design-Expert Software (12.0). The input and output parameters were modeled and validated using Artificial Neural Networks (ANN) based on 40 experimental data generated by the OD. The optimum bio-oil yield of 15.6 wt. % was obtained at 650 °C, 30 min, and 1 mm particle size. The Correlation Coefficient (R2) of the model for the bio-char and bio-oil yield under the OD were 0.998 and 0.996, respectively. The optimized ANN architecture employed the in-built Levenberg-Marquardt training algorithm in MATLAB software. Random division of the data into training, validation and testing sets followed 70:15:15 percentage proportions with 15 hidden layers. This resulted in the minimum Mean Square Error (MSE) of 2.15e-05 and (R2) of 0.96394 for the bio-oil yield. The FTIR spectra indicated that bio-oil contained phenols, esters, and acids compound while its Gas Chromatography analysis showed the presence of pyrrolidine, pyrimidine, and aldehydes. These properties signified the bioenergy and biochemical capabilities of the pyrolytic oil obtained. The prediction accuracy indicates that both the ANN and OD can be deployed for accurate prediction.
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.
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.
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°.
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).
Unsteady performance of degraded compressor and turbine blades of an aero-engine at varying ambient and turbine inlet temperatures
(FETiCON, 2023-08-04) I. O. Otaiku; I. O. Otaiku
The paper presents the modelling of unsteady performance of a degraded 4-stage compressor and single stage gas generator turbine blades of PT6T turboshaft aero-engine of a helicopter. The two sections were set as control volumes for analytical and numerical modeling. Numerically, The blade specimens (NACA 65 series) were developed using SOLIDWORKS 20 and simulations performed with FLUENT in ANSYS 20.0. The RANS (Reynolds-averaged Navier–Stokes) equations with Shear Stress Transport model SST (k-w) were chosen for the unsteadiness of pressure and temperature distributions over different levels of reductions in surface area of the blades’ pressure side. 900 x 103 mesh elements size were selected and the boundary conditions-inlets for the two control volumes were 295-325 K and 1083 – 1245 K for compressor and turbine respectively. Analytically, equations for different levels of degradations (surface area reductions) were developed to determine their flow performance at new pressure and temperature for compressor (∆P_2C,∆T_2C) and turbine (∆P_3T,∆T_3T) with change in time and the corresponding rise in centrifugal stress. Results from FLUENT predicts the performance of the sections for 10% surface area reduction with complex structure in the turbulent flow imposes high fatigue stress, hence shows the highest closeness to surge margin. For the compressor, the result emphasizes the impact of inlet conditions on degraded blades over exit conditions. Also in the turbine, velocity contour shows adverse/backward flow as a result of high turbulence formation and rising fatigue due to change in exit pressure flow from stage to stage in the compressor. This exit pressure determines the TIT in the turbine which is a function of efficiency of the single stage gas generator turbine and is crucial to the overall efficiency of the engine and the safety of the engine as a whole. In conclusion, the inter-component flow behaviour between the degraded compressor and turbine as revealed in this study shows the near real-life situation of the engine performance. Summarily, the accurate engine life estimation can be deduced from TIT rising from 1100-1200 K and centrifugal stress 60MN/mm2.
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.
Modeling the unsteady wake of an impulsively started circular cylinder using refined potential flow theory
(IOP Publishing Ltd, 2024) Amoloye, Taofiq Omoniyi
Cylindrical structures find usage in many engineering applications including tethered oil drums and engine canisters slung beneath helicopters in flight. The motion of air around such circular cylindrical structures and the helicopter presents interesting phenomena including flow separation, wakes and turbulence. The physics of these are enshrined in the continuity equation and the Navier–Stokes equations. Therefore, their studies are not only important in mathematics and physics, but they are also required for efficient helicopter operations. In practice, reduced-order models of these operations that take in aerodynamics models of the tethered loads are utilized for stability analysis, flight certification and pilot training because of the prohibitive cost of experimentation and computational analyses of these configurations. However, there is a dearth of realistic analytical models of finite cylinder flows because of the Navier–Stokes problem. Classical potential flow theory provides an avenue to develop such models, but the extant gaps in its predictions significantly preclude its usage for engineering applications. Attempting to bridge these gaps, this article introduces refined potential flow theory in which the governing equations and boundary conditions are satisfied. Viscous effects, fluctuations of the mean flow and three-dimensional effects are also incorporated. For characterization, refined potential flow theory is employed on an incompressible flow over an impulsively started circular cylinder for Reynolds numbers and non-dimensional times in the range 30 < Re < 10^4 and 0.2 ≤ T ≤ 77, 047 respectively. There is an excellent prediction of 0.209 for the Strouhal number at Re = 3, 900. At this transitional Reynolds number, the harmonics of the Strouhal frequency are also captured, and the characteristic irregular fluctuations at sub-Strouhal frequencies are discernible in the velocity spectra. As the flow becomes more turbulent, these become more pronounced at Re = 9, 500 when the predicted Strouhal number is within 10% of experimental result. In the fully developed stage, spectra analyses of the wake velocity components at some downstream locations also display Kolmogorov's Five-Thirds law of homogeneous isotropic turbulence. The present model can thus aid the development of reduced-order models of helicopter operations that feature tethered cylindrical loads.
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.
The Influence of Thermophysical Properties on The Heat and Flow Characteristics of a NanoLubricant Based on Aluminum Oxide
(International Journal of Engineering Research & Technology, 2024-12-07) Itabiyi, O. E.; Sangotayo, E.O; Muraina, A. B.; Akinrinade, N.A.; Sulaiman A. O.; Olojede, M.A.
The potential of nano-lubricants to improve heat transfer and flow characteristics in a variety of engineering applications has motivated a significant amount of interest in the study of their thermophysical properties in recent years. This paper examined the influence of thermophysical properties, including thermal conductivity, viscosity, density, and specific heat capacity, on the heat and flow behavior of aluminum oxide (Al₂O₃)-based nanolubricants that are flowing through a cylindrical channel. The governing equations for momentum and energy were converted to non-dimensional form and solved using a finite difference scheme that was implemented in C++. The analysis examined the impact of thermal conductivity (0.3<κ<1.5), viscosity (0.001<μ<0.3), density (998< ρ <3592), heat capacity (1100 < Cp < 4200), and the Eckert number (1.0
An Evaluation of Predictive Modeling and Error Analysis for Physicochemical Characteristics of Gasoline-Bioethanol Blends in a Gasoline Engine
(American Journal of Engineering Research (AJER), 2024-12-07) Ogunsola A. D.; Alajede A. M.; Olafimihan E. O.; Sangotayo E. O.; Aderibigbe A. A.; Sulaiman A. O.
The integration of bioethanol into gasoline blends has gained significant attention for improving engine performance and reducing environmental impacts. This study evaluated predictive modeling and error analysis of the physicochemical characteristics of gasoline-bioethanol blends (E0, E5, E10, and E15) in a four-stroke gasoline engine. The importance of optimizing blend ratios for efficiency and sustainability underscores the relevance of this research. The physicochemical characteristics, including cetane number, viscosity, density, carbon residue, and heating values, were measured using a data logger and analyzed across blend ratios ranging from 0% to 15%. Profiles of these characteristics were created to assess their relationship with bioethanol content. Predictive models were developed using SAS software, with R-squared and RMSE values evaluated as performance metrics to assess model accuracy and fitness. The results indicate that the coefficient of performance (COP) demonstrated higher sensitivity to bioethanol content in the 0-10% range, stabilizing about10%, suggesting an optimal blend ratio of around 10%. Brake power efficiency decreased linearly with increasing bioethanol content due to the lower energy density of higher ethanol blends. However, the enhanced combustion efficiency of bioethanol compensated for some efficiency losses. Notably, the E10 blend achieved the highest brake power of 391.65 W, Model evaluation revealed robust predictive capabilities, with R-squared and RMSE values for COP at 0.964 and 0.585, respectively, and for braking thermal efficiency at 0.996 and 0.133, respectively. These metrics confirm the model's high accuracy and reliability in predicting engine performance characteristics across blend ratios. Future research should explore the impact of higher ethanol concentrations on engine durability and further optimization of bioethanol-gasoline formulations for enhanced sustainability and effectiveness.

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