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Examinando Ingeniería Aeronáutica por Materia "Aerodinámica"
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- ÍtemAnálisis aerodinámico computacional de dispositivos de punta de ala en la aeronave Vultur(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Torres Suárez, Dina Vanessa; Rojas Olaya, Deisy Janeth; Vaca Ríos, John JairoThis project contains the step-by-step procedure of the analysis and comparison of results through the use of Computational Fluid Dynamics (CFD) whose main purpose is to determine which of the three configurations designed (wing clean, wing winglet, wing tiptank) for the Vultur aircraft allows to obtain greater performance and efficiency taking into account the needs under which it was designed based on the requirements established by FAC (Fuerza Aérea Colombiana). In turn, the theoretical foundations of the CFD will be shown in general, used as a fundamental basis in the development of the project, in addition the design characteristics determined for the prototypes and their elaboration in 1:10 scale will be observed that will allow a clearer guide to the objects of study of the project throughout its development. This report will provide tables and figures that show the analysis process at each stage, which were essential to determine which of the three configurations provided better performance and efficiency of the Vultur aircraft, from which it was established that the wing winglet provides a better contribution to the aircraft in terms of the study parameters. Finally, the conclusions obtained at the end of this project and recommendations for future research projects based on the design and aerodynamic analysis of wingtip devices or improvement of the results obtained will be presented.
- ÍtemAnálisis aerodinámico computacional de una superficie hipersustentadora en el borde de la salida de un plano(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Nova Gomez, Edward Mateo; Ávila Granados, Diego LeonardoIn this project, a high-lift device will be designed; it will be located in the upper rear section of the aerodynamic airfoil, in the area known as the extrados. The aim is to know the behavior of the airflow in the presence of the mentioned device, considering that it will have the ability to move both longitudinally and vertically; the analysis will be carried out through simulations in the software ANSYS Fluent. Based on the results of the simulations, the aerodynamic behavior will be analyzed, determining the effectiveness of the high-lift device in the main stages of flight, such as take-off, landing and cruise flight. Due to the importance of hyper-lift surfaces in an aircraft, it is required a configuration that increases the lift in the take-off phase, keeping drag as low as possible, this together with a landing configuration that generates high lift along with a high drag index, and finally allow the highest lift/drag ratio to be achieved in the cruise phase. The previous scenarios will be an indication of the efficiency of the design to be studied
- ÍtemAnálisis aerodinámico de una turbina de eje vertical para la implementación en la Fundación Universitaria Los Libertadores(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Aguilar Salinas, Nicole Tatiana; Florez Guzmán, Julian Fernando; Rodríguez Avellaneda, Jeimy Tatiana; Rolón Ríos, Juan Eduardo
- ÍtemAnálisis de performance para una aeronave Stol tipo CommuterGómez Garavito, Jan Carlos; Bermudez Arroyo, Omar Guillermo; Gonzalez Cruz, Francisco Javier
- ÍtemAnalisis numérico de la estructura de chorros supersónicos utilizando OpenFOAM.(2024-02-05) Gutiérrez Marcantoni, Luis Felipe; Melo Dazav, Pedro Fernando, Co-Director; Rodríguez Barón, Ivan Felipe , Co-DirectorEste proyecto se centra en la investigación numérica del flujo supersónico generado por un chorro que se expande libremente. Se desarrollan simulaciones para una configuración específica, la experimental estudiada por Ladenburg que cuenta con datos para contrastar. Esta configuración se representa a nivel computacional empleando un dominio rectangular sobre el cual el chorro se expande a través de una región de entrada con diámetro ($D$), considerando diferentes relaciones de expansión y llevando a cavo contrastes con los resultados experimentales de la estructura del chorro y comparaciones de parámetros como la ubicación del primer disco de Mach. Además se analiza la evolución del flujo mostrando distribuciones de las diferentes variables de interés comentando su comportamiento resaltando como su evolución se corresponde con la teoría del flujo supersónico.Para obtener los resultados aquí presentados se utilizó el \emph{solver} \verb+rhoCentralFoam+ del paquete de código abierto \openFoam. Por lo que no solo se incorporan en el trabajo los fundamentos teóricos necesarios para explicar la estructura de un chorro sino que también elementos de las herramientas numéricas utilizadas.
- ÍtemAnálisis y validación aerodinámica para el vehículo monoplaza de competición eléctrico de la Escudería DCM para la Fórmula Sena 2014Flórez López, Gustavo Adolfo; Guzmán Bohórquez, Rolando; Vaca Rios, John Jairo
- ÍtemCaracterización aerodinámica de un tractocamión(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Garzón Hernández, Bryan Steven; Murillo Castellanos, Jhonatan Yesid; Vaca Ríos, John JairoThe present investigation was made with the objective of aerodynamically characterizing the truck, implementing aerodynamic complements by altering the air ow that passes over the surface of the truck, influencing the pressure coefficient, aerodynamic drag and other aerodynamic phenomena that occur affecting its performance. A scientific method was implemented, selecting the prototype from reports of cargo vehicles in Colombia published by FENALCO and ANDI between 2017 and 2018, after the truck design and the aerodynamic complements were made in the Solid Edge ST9 software which were manufactured on a scale of 1: 21.3. The manufacture of the cabin, rims and complements was made by 3D printing and the trailer in balsa wood and MDF, using the technique of serial plan. After the model was fabricated, experimental tests were carried out in the wind tunnel of the Fundación Universitaria Los Libertadores. Initially, tests were carried out with the standard truck and afterwards different aerodynamic kits were implemented, obtaining as a result the pressure coefficient distribution figures through the upper section of the vehicle. Flow visualization tests were carried out by means of injected smoke and mercerized cotton (tufts), with this it was possible to show how was air behavior on the truck, identifying the critical points that affected it aerodynamically speaking. Additionally, an aerodynamic - mathematical analysis was carried out, concluding which complement offered a greater percentage of reduction in critical points of the pressure coefficient, thus increasing the aerodynamic efficiency of the truck. On the other hand, this test was able to verify and compare the data obtained and plotted in the tests mentioned above, finally concluding that the Kit that offered the best performance and therefore greatly reduced a critical point in the pressure coefficients on the tractocamión was Kit 1.
- ÍtemComparación metodológica del diseño de un planeador en forma de ala volante.(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Estupiñán Cocunubo, Duván Arturo; Russi Moreno, Brandon Nicolas; Jaime Enrique Orduy RodríguezThe development of the aeronautical industry has been framed with the continuous design and improvement of aeronautical products, however, design methods have been standardized in such a way that beginner or inexperienced designers tend to be guided by the methodological processes presented by recognized authors like Raymer and Roskam. However, when guided by these methodological processes, important aspects of design such as innovation and constant contact with customers (stakeholders) in product development are lost, therefore, it is necessary include in the research the use of a methodology that unifies the customer's need with the development of the design, where consistent traceability between variables and components can be verified and carried out. For this reason, the methodology presented by Systems Engineering (SE) is analyzed as it couples interaction with customers with the emergence of innovative ideas. This document aims to make a comparison between traditional methodologies with the methodology presented by the Systems Engineering (SE). This comparison is based on the conceptual development of a planner, from a reference project, which makes use of the methodology of the aforementioned authors and its counterpart designed through Systems Engineering (SE). The development and the respective analysis and comparison are presented, allowing to recognize or agree on the advantages and differences of the use of this methodology in the design of aeronautical components.
- ÍtemConstrucción, integración y pruebas de los subsistemas que conforman el cohete Isaías ISierra Gamboa, Jonathan Ricardo; Loaiza Diaz, Miguel Angel; Reyes Caballero, Diego Armando
- ÍtemDesarrollo de una aeronave no tripulada con detector de metales para la búsqueda de minas antipersonales(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Bautista Pedreros, Jessica Andrea; Gómez Useda, John Alberto; Rodríguez Aldana, Didier
- ÍtemDiseño aerodinámico de un túnel de viento de circuito abierto.(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Rojas Escobar, Manuel Alejandro;; Mendez Moreno, AurelioA wind tunnel is a tool that allows develop experiments within a controlled air flow to analyze the interaction of different elements with the air. This project makes an approach from the aerodynamic point, to design for a high speed, open circuit wind tunnel; the parameters to design are: a large test section enough to allow access a person for the installation and develop the models testing. For this design I adopting the recommendations made by the authors to optimize the uniformity flow in low speed wind tunnel and additionally I make use of a CFD (Computational Fluid Dynamics) as support in selecting the profile and length contraction. The CDF plays an important role to make an approach to behavior of the flow inside the tunnel, which allows you to make suggestions for improving the configuration of the wind tunnel within the range of operation. The wind tunnel is based in calculating the air properties, a maximum speed within test section equivalent to 0,6 basing the design on atmospheric standard conditions for a height equivalent to that of the Bogota city (2.600m). Within this work I also include the preselection of the instrumentation needed for the measurement of the basic variables in the development of a test of aerodynamics in a wind tunnel (pressure, speed and temperature).
- ÍtemDiseño conceptual de un mecanismo para el montaje objetos de estudio en la sección de prueba de un túnel de choque supersónico(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Balaguera Moreno, Carlos Antonio; Caballero Caicedo, Joseph Camilo; Orduy Rodríguez, Jaime EnriqueThis project presents the conceptual design of a mechanism for assembling study objects in the test section of a shock tunnel, under development by the Los Libertadores University Foundation for the major project, on the first shock tube carried out in Colombia. Thanks to the controlled tests that can be carried out with a tool such as a supersonic wind tunnel, extreme aerodynamic phenomena could be studied that would greatly help new knowledge. The document will present the aforementioned conceptual design, organized as follows: the introduction to wind tunnels, how they are and have been throughout history a very useful tool in the study of existing aerodynamics; The approach to the problem was developed, taking into account a proper investigation on the study of aerodynamics in Colombia and how from this document it is desired to generate great engineering progress; The methodology proposed to carry out the design of the aforementioned mechanism took into account previous works and the objectives set. For chapter 1, a referential framework was developed from which all the previous concepts were studied. Then, through the proposed methodology, carry out an investigation developed in the following chapters: Chapter 2. Definition of functional requirements; Chapter 3. Exploration of possible solutions and selection of the mechanism; Chapter 4. Analysis and selection of materials; Chapter 5. Conceptual design and CAD representation; Chapter 6. Structural analysis
- ÍtemDiseño conceptual y preliminar de una aeronave categoría transporte regionalGrass Nuñez, Johan Sebastian; Robayo Cachay, José Albeiro; Rincón Ruiz, Sergio Esteban; Gamba Torres, Juan Carlos
- ÍtemDiseño conceptual y preliminar de una aeronave militar para entrenamiento y ataque ligero: Horus at-9(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Tibaduiza Landínez, Howard Stevenson; Fadul Aguirre, EduardoThis document is defined for the design process of a military aircraft within the category of advanced training and light attack, for two crew members. This process is limited to the phases of the design, you will obtain results that will be necessary for the initial initials (in the conceptual design phase), of the limitations of the design to make this something viable as to what needs to be fulfilled (in the preliminary design phase), without oversizing the capabilities of the aircraft. Throughout the development of this document, you will find typical design tools that are necessary to fulfill the overall objective of the project. In general, three fundamental aspects are used: the baseline, the RFP and the design methodology. The baseline is compulsory used in the design of aircraft to obtain values that determine statistical design behaviors that at a conceptual level allow parameterizing the study aircraft
- ÍtemDiseño conceptual, preliminar y análisis CFD de un avión jet ultra ligeroPulido Gonzalez, Anyelo Andrés; Flores Linares, Michael; Bravo Mosquera, Pedro DavidThe conceptual and preliminary design of an very-light jet (VLJ) is presented, covering all the concepts and design requirements that define the configuration of the aircraft, so that it is competitive in a promising market. Traditional methods of aircraft design were used to develop and analyze the suitability of the aircraft, seeking to improve aerodynamic efficiency byproposingtheimplementationofdifferentconfigurationsofwingletsinstalledatthetipsof the wings. The project addressed the study of size, weight, pilot ergonomics, aerodynamics, stability, systems, subsystems and performance. Later, computational analytical methods were used to design each of the components of the aircraft, together with the winglet deviviii ces, also called "Blended winglet", characterized by having the fin twisting towards the rear and a convenient incline with reference to the aircraft. Four winglet configurations were created, each one modifying the CANT angle and the wing span,todeterminetheaerodynamiccharacteristicsofferedbyeachofthemthroughastudyof computational fluid dynamics (CFD), solving the Reynolds-Averaged-Navier-Stokes(RANS) equations, using the turbulence model Shear Stress Transport (k-w). The parameters of the simulations were assumed based on the maximum operating altitude, studying exclusively the flow around the clean wing, winglet configurations and in the whole aircraft, in the most critical conditions before and after installing the devices. The coefficients of lift, induced drag, parasite drag, total drag and aerodynamic efficiency were analyzed. The results were fulfilled and validated, demonstrating that winglet devices remain the most promising alternative to improve the aerodynamic performance of the verylight jet.
- ÍtemDiseño de un alerón delantero para un kart de competencia mediante CFDPacheco Martínez, Karen Gisell; Rojas Sarmiento, Oscar Daniel; Vaca Ríos, John JairoThe following document shows the analysis, redesign and aerodynamic validation processes of a competition kart through the Computational Fluid Dynamic with the purpose of evaluating its performance before and after of the realized modification to its original design and thus improve its performance during a competition. Based on the CFD theory and orienting this same to one of its most common uses, like is the external flow study around a car; modeling of the kart was carried out using the Solid Edge software and Inventor software, one of these modeling was using the common design and the other was using an incorporated aileron, this aileron was made through an aerodynamic airfoil chosen for its efficiency using the XFLR-5 software. Later, through the Ansys Workbench 19 software the computational domain was designed, taking into account different meshing settings, boundary conditions and solution methods; then, a series of results were obtained for each kart modeling and then, through analysis, a final conclusion could be established taking into account the perspective of different academic articles with related topics. Also, recommendations and necessary suggestions are provided to carry out
- ÍtemDiseño estructural y aerodinámico de un monoplaza formula Sena EcoHernández Martín, Juan Camilo; Velandia Bautista, Jonathan Camilo; Vaca Rios, John Jairo
- ÍtemDiseño preliminar y conceptual de aeronave no tripulada para monitoreo de actividad volcánicaBravo Mosquera, Pedro David; Uribe Agudelo, Alvaro; Martins Abdalla, Alvaro
- ÍtemDiseño, construcción y puesta en funcionamiento del túnel de viento subsónico de circuito abierto de la Universidad Nacional de Colombia sede Bogotá con implementación de sistemas de toma de datos de aire y visualización de flujo(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Arango Duque, Alejandro; Yepes Murillo, Johanna Marcela; Murcia Piñeros, Jhonathan OrlandoThe document developed below records the detailed design, construction, commissioning, installation of equipment for visualization and data collection of the open-circuit wind tunnel with closed testing section of the National University of Colombia, Bogotá headquarters During the design stage a theoretical analysis is implemented that is corroborated by means of finite element analysis (FEA), and computational fluid dynamics (CFD) for structural components and flow behavior respectively . Giving way to the construction parameters involved in the selection of materials and manufacturing processes that are evaluated in the commissioning; until covering the resulting stages achieving an operational viewing tunnel In the design and construction phase, the National University of Colombia indicates a power restriction of 0.66 kW, which includes the technical specifications of the electric motor made available from a previously implemented wind tunnel. Likewise, the dimensions of 0.30m by 0.30m are highlighted for the cross section of the test area, taking as a precedent the previous chamber, which is indeed an experimental alternative for the new wind tunnel. Under this last requirement, the tunnel is designed with a modular configuration that allows easy movement with the practicality of changing sections.
- ÍtemDiseño, desarrollo y pruebas del sistema de recuperación para el cohete sonda LIBERTADOR I.(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Castillo Vargas, Leudy Eliana,; Jiménez Chocontá, Nixon Alexis;; Murcia Piñero, Jhonathan OrlandoThe purpose of the project is for the Liberator I rocket to be recovered and have a controlled descent with the lowest possible impact speed, by means of a system that reduces the rate of descent for the impact on the Earth's surface by means of a drop-down and ejectable parachute that present a greater drag force, a smaller projected area and a smaller volume, complying with the design requirements of the Liberator I rocket. Due to the above, the following research question is posed: How should the design and construction of the recovery system be so that meet the requirements of the Liberator I rocket probe