Department of Aeronautic Engineering

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Wind Engineering: A Review of the Eurocode provisions for the Wind Loading on Low-rise Buildings
(Cranfield University, 2012-09) Amoloye, Taofiq Omoniyi
Building codes such as the Eurocode have usually been used as a cheaper alternative to wind tunnel studies in the consideration of wind loading on a structure. It is often the case that very tall buildings and large structures have enough economic justification for expensive wind tunnel studies in their design stage. Such wind tunnel studies, as per state-of-the-art, feature simultaneous scanning of and acquisition of loading data from hundreds of pressure tappings with subsequent high-speed computer data processing and analysis. This is not the case for low-rise buildings which do not find their way into the wind tunnel except in the case where they are unusual edifices. Low-rise buildings, however, are the most damaged in wind storms. In addition, in the present times, their shapes are increasingly losing touch with the traditional and generic forms dealt with in the Eurocode. Therefore, the question is: How well does the Eurocode, which was put together with information from wind tunnel studies performed in the 50s and 70s using currently outdated data acquisition techniques, deal with present building shapes? The study was based on models of a simple cuboidal building; a quasi-rectangular building with inset faces in its plan; and a building plan featuring a re-entrant corner possessing curved surfaces at the internal and external junctions of its wings. It was concluded from the results of the study that adapting the Eurocode wind loading provisions to irregular building plans characteristic of modern times gives very unsafe solutions. The variations of pressure with wind direction on the internal walls of the wings of and the curved surface at the internal junction of the re-entrant corner were observed to follow coherent wave forms which are mutually similar. These call for further research.
A POSTGRADUATE WORKS EXPERIENCE REPORT TO THE NIGERIAN SOCIETY OF ENGINEERS
(2014) Amoloye, Taofiq Omoniyi
I prepared this 47 page report in partial fulfilment of the requirements for admission into the corporate membership of the Nigerian Society of Engineers and towards the goal of registration with Council for the Regulation of Engineering in Nigeria. Corporate membership of the Nigerian Society of Engineers is only attained after passing a series of thorough assessment including but not limited to an oral interview, a written examination and submission of a technical report. The report contains two volumes: Volume I which details my postgraduate experience; and Volume II which gives the details of the design and construction of a hot air balloon which I undertook between 2013-2014.
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.
A Refined Potential Theory for the Incompressible Unsteady Subcritical-Reynolds number Flows on Canonical Bluff Bodies
(2020-11-16) Taofiq O Amoloye
The three main approaches to exploring fluid dynamics are actual experiments, numerical simulations, and theoretical solutions. In classical potential theory, the steady inviscid incompressible flow over a body can be obtained by the superposition of elementary flows with known analytical solutions. Analytical solutions can offer huge advantages over numerical and experimental solutions in the understanding of fluid flows and design. These advantages are in terms of cost and time consumption. However, the classical potential theory falls short of reconciling the actions of viscosity in an experimentally observed flow with the theoretical analysis of such a flow. As such, it is unable to resolve the boundary layer and predict the especially important flow separation phenomenon that results in the pressure drag experienced by a body in the flow. This has relegated potential theory to idealized flows of little practical importance. Therefore, an attempt is made in this thesis to refine the classical potential theory of the flow over a circular cylinder to bridge the gap between the theory and experimentally observed flows. This is to enhance the ability to predict and/or control the flows' aerodynamic quantities and the evolution of the wake for design purposes. The refinement is achieved by introducing a viscous sink-source-vortex sheet on the surface of the cylinder to model the boundary layer. These vortices, sources and sinks introduced at the cylinder surface are modeled as concentric at every location. The vortices are modeled as 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 and time-dependent stream function that captures critical qualitative features of the flow including flow separation, reattachment, wake formation, and vortex shedding. After that, a viscous potential function, the Kwasu function, with which the pressure field is obtained from the Navier-Stokes equation, is derived from the stream function. It is obtained by defining the viscous stream function on a principal axis of the flow about which the vorticity vector is identically zero. Strategies have also been developed to account for the finite extent of the cylinder and dynamic unsteadiness of the flow, and to predict the points of separation/reattachment/transition and the boundary layer thickness. Additionally, the strategies are used to obtain forces and apply the solution to arbitrary geometries focusing on spheres and spheroids. These strategies include the gravity analogy that considers a fluid element-cylinder scenario to be like a two-body problem in orbital mechanics. This analogy introduces the perifocal frame of fluid motion and exploits it to resolve the d'Alembert's Paradox. The perifocal frame is also used to predict flow separation/reattachment/transition and explain the observation of sign changes in the shear stress distribution at the rear of a circular cylinder in a crossflow. The refined potential theory is verified against experimental and numerical data on the cylinder in an incompressible crossflow at freestream Re∞=3,900. Its drag prediction is within the error bound of measured data and tHRLES (transitional Hybrid Reynolds-averaged Navier-Stokes Large Eddy Simulation) prediction. The predictions of the pressure distribution, separation point and Strouhal number are also within acceptable ranges. Its prediction of the force coefficients over the range 25≤Re∞<300,000 is validated against experimental and theoretical data on the cylinder in crossflow. There is a good agreement in the magnitude and trend for Re∞>100. For Re∞<100, there is a disparity in magnitude that is unsafe for design purposes. Similarly, it under-predicts the coefficient of drag in some of the explored axial flow configurations. However, at Re∞=96,000 and an aspect ratio of 2, the RPT drag prediction falls within 1.2% of validated computational result. The energy spectra of the wake velocity display the Kolmogorov's Five-Thirds law of homogeneous isotropic turbulence. This verifies and validates the unsteadiness in refined potential theory as turbulent in nature. The drag coefficient of a sphere for 25≤Re∞< 300,000 is explored to demonstrate the application of refined potential theory. Additionally, the flow over a sphere at Re∞=100,000 is explored in detail. A generally good agreement is observed in the prediction of the experimental trend for Re∞≥2,000. The transitional incompressible flows over a 6:1 prolate spheroid at an angle of attack β=45° for Re∞=3,000$ and Re∞=4,000 are also explored. The present theoretical pressure distribution has a close agreement with the DNS (direct numerical simulation) result in the starboard rear of the spheroid. However, the magnitude of the predicted force coefficients are generally less than five times the corresponding DNS results. The asymmetry of the DNS pressure distribution in the meridian plane is not captured. Therefore, further analyses of the spheroid flow including the separation locations are recommended for further studies. It is concluded that the refined potential theory can be used to resolve, explore and/or control the aerodynamic quantities of the flows around canonical bluff bodies as well as the evolution of their wakes.
A Refined Potential Theory for the Incompressible Un- steady Subcritical-Reynolds number Flows on Canonical Bluff Bodies
(Georgia Institute of Technology, 2020-11-19) Amoloye, Taofiq Omoniyi
The three main approaches to exploring fluid dynamics are actual experiments, numerical simulations, and theoretical solutions. In classical potential theory, the steady inviscid incompressible flow over a body can be obtained by the superposition of elementary flows with known analytical solutions. Analytical solutions can offer huge advantages over numerical and experimental solutions in the understanding of fluid flows and design. These advantages are in terms of cost and time consumption. However, the classical potential theory falls short of reconciling the actions of viscosity in an experimentally observed flow with the theoretical analysis of such a flow. As such, it is unable to resolve the boundary layer and predict the especially important flow separation phenomenon that results in the pressure drag experienced by a body in the flow. This has relegated potential theory to idealized flows of little practical importance. Therefore, an attempt is made in this thesis to refine the classical potential theory of the flow over a circular cylinder to bridge the gap between the theory and experimentally observed flows. This is to enhance the ability to predict and/or control the flows' aerodynamic quantities and the evolution of the wake for design purposes. The refinement is achieved by introducing a viscous sink-source-vortex sheet on the surface of the cylinder to model the boundary layer. These vortices, sources and sinks introduced at the cylinder surface are modeled as concentric at every location. The vortices are modeled as 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 and time-dependent stream function that captures critical qualitative features of the flow including flow separation, reattachment, wake formation, and vortex shedding. After that, a viscous potential function, the Kwasu function, with which the pressure field is obtained from the Navier-Stokes equation, is derived from the stream function. It is obtained by defining the viscous stream function on a principal axis of the flow about which the vorticity vector is identically zero. Strategies have also been developed to account for the finite extent of the cylinder and dynamic unsteadiness of the flow, and to predict the points of separation/reattachment/transition and the boundary layer thickness. Additionally, the strategies are used to obtain forces and apply the solution to arbitrary geometries focusing on spheres and spheroids. These strategies include the gravity analogy that considers a fluid element-cylinder scenario to be like a two-body problem in orbital mechanics. This analogy introduces the perifocal frame of fluid motion and exploits it to resolve the d'Alembert's Paradox. The perifocal frame is also used to predict flow separation/reattachment/transition and explain the observation of sign changes in the shear stress distribution at the rear of a circular cylinder in a crossflow. The refined potential theory is verified against experimental and numerical data on the cylinder in an incompressible crossflow at freestream Re∞=3,900. Its drag prediction is within the error bound of measured data and tHRLES (transitional Hybrid Reynolds-averaged Navier-Stokes Large Eddy Simulation) prediction. The predictions of the pressure distribution, separation point and Strouhal number are also within acceptable ranges. Its prediction of the force coefficients over the range 25≤Re∞<300,000 is validated against experimental and theoretical data on the cylinder in crossflow. There is a good agreement in the magnitude and trend for Re∞>100. For Re∞<100, there is a disparity in magnitude that is unsafe for design purposes. Similarly, it under-predicts the coefficient of drag in some of the explored axial flow configurations. However, at Re∞=96,000 and an aspect ratio of 2, the RPT drag prediction falls within 1.2% of validated computational result. The energy spectra of the wake velocity display the Kolmogorov's Five-Thirds law of homogeneous isotropic turbulence. This verifies and validates the unsteadiness in refined potential theory as turbulent in nature. The drag coefficient of a sphere for 25≤Re∞< 300,000 is explored to demonstrate the application of refined potential theory. Additionally, the flow over a sphere at Re∞=100,000 is explored in detail. A generally good agreement is observed in the prediction of the experimental trend for Re∞≥2,000. The transitional incompressible flows over a 6:1 prolate spheroid at an angle of attack β=45° for Re∞=3,000$ and Re∞=4,000 are also explored. The present theoretical pressure distribution has a close agreement with the DNS (direct numerical simulation) result in the starboard rear of the spheroid. However, the magnitude of the predicted force coefficients are generally less than five times the corresponding DNS results. The asymmetry of the DNS pressure distribution in the meridian plane is not captured. Therefore, further analyses of the spheroid flow including the separation locations are recommended for further studies. It is concluded that the refined potential theory can be used to resolve, explore and/or control the aerodynamic quantities of the flows around canonical bluff bodies as well as the evolution of their wakes.
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.
Analysis of an Unsteady Incompressible Cross􀂧ow on a Stationary Circular Cylinder at Reynolds number 3,900 Using Re􀂦ned Potential Flow Theory
(Research Square, 2022-06-03) Taofiq O. Amoloye
The motion of a fluid around a circular cylinder presents interesting phenomena including flow separation, wake and turbulence. The physics of these are enshrined in the continuity equation and the Navier-Stokes Equations (NSE). Therefore, their studies are important in mathematics and physics. They also have engineering applications. These studies can either be carried out experimentally, computationally, or theoretically. Theoretical studies of a cylinder flow using classical potential flow theory (CPT) have some gaps when compared to experiments. Attempting to bridge these gaps, this article introduces refined potential flow theory (RPT) and employs it on a stationary circular cylinder incompressible crossflow at Reynolds number 3, 900. It leverages experimental observations, physical deductions and some agreements between CPT and experiments in the theoretical development. This results in the incompressible Eulerian Kwasu function which is a quasi-irrotational stream function that satisfies the governing equations and boundary conditions. It captures vorticity, boundary layer, shed wake vortices, three-dimensional effects, and static unsteadiness. The Lagrangian form of the function is exploited for the flow pathlines that are used to incorporate dynamic unsteadiness. A gravity analogy is used to predict the separation, transition, and reattachment points. The analogy introduces the perifocal frame of fluid motion. The forces are obtained in this frame with a change of variable. The drag prediction is within the error bound of measured data. The RPT pressure distribution, separation point and Strouhal number are also within acceptable ranges. Energy spectra analyses of the wake velocity display Kolmogorov’s Five-Thirds law of homogeneous isotropic turbulence.
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.
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).

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