Pedro David Bravo Mosquera.

O objeto do projeto consiste na análise integrada e detalhada da aerodinâmica e aeroacústica de uma aeronave disruptiva com características de decolagem vertical, voo de transição e cruzeiro horizontal. Para isso, será utilizado o software PowerFlow, que emprega o método de Lattice Boltzmann para simulações CFD transientes de alta fidelidade, em conjunto com o módulo PowerACOUSTICS para avaliar o comportamento aeroacústico. A análise será conduzida em quatro fases progressivas, começando pela aerodinâmica das superfícies sustentadoras e fuselagem em configuração de cruzeiro, passando pela inclusão das hélices horizontais e verticais, até chegar à identificação das fontes de ruído externo e ao estudo de soluções mitigadoras. A partir dos modelos numéricos, serão obtidos coeficientes aerodinâmicos fundamentais para a otimização preliminar do projeto e para o desenvolvimento de ensaios aerodinâmicos em túnel de vento utilizando um modelo completo em escala, com todos os sistemas propulsivos instalados.O projeto busca inovação ao integrar métodos numéricos e experimentais para caracterizar as interações entre os sistemas de propulsão e superfícies sustentadoras em diferentes regimes de voo, incluindo hover, transição e cruzeiro. Ensaios dinâmicos em túnel de vento, realizados com as correções adequadas para o escoamento confinado, fornecerão dados críticos sobre as transições de propulsão vertical para horizontal, incluindo variações no ângulo de ataque e a dependência da sustentação em relação à velocidade. Além disso, o estudo pretende desenvolver soluções para reduzir o ruído externo gerado pelos rotores enquanto se mantém a eficiência aerodinâmica, enfrentando o desafio de balancear desempenho e consumo energético em sistemas de propulsão elétrica. Este projeto pioneiro no país promete contribuir significativamente para o avanço tecnológico na concepção de aeronaves sustentáveis e inovadoras

Projeto visa a construção de um túnel de vento com área de seção 2mx2m para ensaios aeroacústicos e aerodinâmicos. Devera possuir baixo ruído de fundo e a câmara de ensaios tipo aberta será envolta em uma câmara anecoica. A velocidade máxima deverá ser de 65m/s e o nível de turbulência e ruído de fundo 0,15 e 90dBA.Plataforma RME (propulsão distribuída) e modelo ASA ALONGADA

O projeto proposto estabelecerá uma estrutura e modelos para modelar a interação motor/aeronaves, incluindo grandes consumidores de energia na aeronave, a fim de realizar estudos de trade-off com o objetivo de alcançar o objetivo do projeto de encontrar combinações ótimas aeronave/motor. O projeto usará uma metodologia consistente de design conceitual para fazer estudos detalhados de trade-off. O modelo da aeronave (WP2) será baseado em conhecimento acadêmico e literatura aberta apoiada pela Saab para relevância. O trabalho principal no WP2 será feito pela USP no Brasil e será iterado com Saab e Chalmers (universidade) para corresponder, por exemplo, a interfaces do modelo. O modelo de motor (WP3) tem sua origem em modelos de motores militares existentes desenvolvidos pela Chalmers. A Chalmers e o doutorando irão, no projeto proposto, desenvolver ainda mais o modelo do motor e adaptá-lo para futuras necessidades de aeronaves de combate.

This project deals with the conceptual design and optimization of a
medium STOL (Short Take-off and Landing) tactical transport aircraft,
which is intended to expand the institutional capabilities of the
Colombian Air Force (FAC) in terms of versatility and flexibility. A multifidelity design strategy was developed during the conceptual design
stage of the aircraft, combining classical methodologies and high-fidelity
Computational Fluid Dynamics (CFD) simulations. This methodology
allowed the aircraft to be assessed in a single design space, based on its
design requirements, mission and applicable airworthiness standards. The optimized aircraft is compared to major competitors in order to discuss and highlight its main advantages and feasibility for future production.

Nowadays, due to technological evolution as well as several green aerospace projects, the aeronautical community is implementing advanced design strategies looking for the next future airliner configuration. The use of significant technology breakthroughs in the area of aircraft design allows the identification of large-scale aerodynamic data to understand the aircraft performance and its implication to mitigate the undesirable impact of airliners on the environment. In order to achieve ambitious goals, non-conventional solutions have attracted the attention of designers, highlighting the closed non-planar wing configurations, which have shown a reduction in pollutant emissions by minimizing the induced drag, in addition to presenting several advantages when compared to conventional designs, such as a reduced empty weight and a better aerodynamic efficiency. Likewise, boundary layer ingestion (BLI) has emerged as a potential propulsion concept for future aircraft configurations, mainly by reducing wasted kinetic energy in the exhaust jet, due to the lower wake velocities obtained by the combination of the aircraft wake along with the propulsor jet, thus reducing cruise energy consumption and CO2 emissions. Based on the aforementioned approaches, this investigation intends to combine the potential benefits of a closed-wing configuration with a BLI propulsion system in order to develop a modern and advanced civil transport aircraft. During the conceptual design phase, a novel computer-based design method is developed in order to determine the main geometric, aerodynamic, stability and performance characteristics of the aircraft, based on its design requirements and constraints. Once obtained a baseline concept, a scale-model will be manufactured in order to perform a back-to-back wind-tunnel analysis of non-boundary layer ingesting and boundary layer ingesting versions of the aircraft. Finally, the aerodynamic design optimization will take place through a computational fluid dynamics (CFD) formulation, using continuous adjoint methods and incorporating a gradient-based optimizer. It is expected that such data will be useful in interpreting that a closed-wing aircraft coupled to a BLI propulsion system can meet the demands of future aviation.

The conception of non-conventional aircraft to achieve a certain performance or operational improvement is undoubtedly, one of the most important objectives of the aeronautical engineering. This work presents the conceptual design and the intake aerodynamic analysis of a non-conventional aircraft whose main design feature is an inverted-rectangular dorsal intake with external compression, followed by a three dimensional transitioning S-duct diffuser with circular cross section at aerodynamic interface plane. An in-house presizing tool was developed to define the key layout characteristics and select the optimal airframe-engine combination regarding the design requirements of the aircraft, whereas Reynolds-averaged Navier-Stokes (RANS) simulations were also conducted to assess the performance of the intake-airframe integration at several flight conditions. The results found in this work were evaluated separately. First, the analytic design method of the intake itself was compared with numerical simulations in order to check and maximize the total pressure recovery at on-design condition. Subsequently, the intake-airframe integration assessment took place, showing that adequate performance and compatibility characteristics are maintained during subsonic and transonic maneuvers. However, at supersonic velocities, the flow expansion on the fuselage and wings produced an increase in the local Mach number which reduce the intake performance levels. These studies provided an extensive data to evaluate the effects of specific aircraft design variables on dorsal intake performance, such as the integration of the cockpit, the boundary layer diverter, and several delta wing configurations. All numerical results show that, dorsal intakes are a promising alternative for aircraft that require only reasonable supersonic maneuverability capabilities and high subsonic and transonic capabilities. In addition, dorsal intake coupled to S-duct diffuser provide line-of-sight blockage of the engine blades, satisfying the requirement of low radar signature, lightweight and low drag of the next generation of fighter aircraft.

When volcanoes manifest unusual signs of activity, real-time data aids for evaluating and communicating reports about volcanic hazards. For this reason, the present research aims the aerodynamic design of a low-cost unmanned aerial vehicle (UAV) able to perform aerial surveillance of volcanic environments. Its main mission is to transmit real-time volcanic data to a remote location, in order to aid to forecast volcanic eruptions, as well as avoiding the exposition of pilots and scientists to these dangerous flight conditions. During the conceptual design phase, classical and new design procedures were developed in order to determine the vehicle design requirements, in relation to its flight in a hard scenario like an active volcano. Likewise, the main geometric, aerodynamic, stability and performance parameters of the UAV were calculated and assessed through theoretical/analytical presizing and Computer-aided Design (CAD) methods. After obtaining the final concept, the aerodynamic design was carried out considering the constraints found in the previous design phase. In this way, an accurate estimation of the aerodynamic coefficients was developed, through analytical simulations, Computational Fluid Dynamics (CFD) simulations and wind tunnel testing.
Results showed that the entire design process was consistent because the analytical, numerical and experimental results were greatly similar in the Lift and Drag coefficients. Furthermore, the UAV characteristics are within the limits of the design requirements, presenting several aerodynamic and performance advantages in comparison to other vehicles used in the same mission. This suggested that, on a large scale, the aerodynamic behavior of the UAV is suitable for performing the mission for which it was created. However, actual-environmental studies are still necessary in order to validate the reliability of the designed UAV.