Optimization of a Bi-dimensional Intake for a Supersonic Aircraft Using a Genetic Algorithm

• Autor(a) principal: Simão, Diogo Rafael Ribeiro Pinto
• Data de Publicação: 2022
• Tipo de documento: Dissertação
• Idioma: eng
• Título da fonte: Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos)
• Texto Completo: http://hdl.handle.net/10400.6/13017
• topic: Conduta; 2-D; Admissão Supersónica; Bidimensional; Choques Normais; Choques Oblíquos; Design; Otimização; Projeto; Domínio/Área Científica::Engenharia e Tecnologia::Engenharia Aeronáutica

Since the beginning of jet flight, the intake has been subject to many studies due to its importance. From its position on the wings, in the wing root, nose and being mounted on the fuselage, many decades were spent on the research and solution of constraints. These are still present in the form of space and weight saving, lower drag, centre of gravity, lower radar visibility, etc. Although theoretically intakes with an infinite number of weak shocks are better, these fail to produce better results. An intake with small number of shocks is preferred as it is smaller in size, thus saving weight, and has better off-design performance. In the present work, a bi-dimensional mixed compression intake is designed having the Panavia’s Tornado engine requirements in mind and the aircrafts performance values. The designed intake results were in line with other studies. A comparison is made between the parametrical result and the results of a genetic optimization algorithm to minimize length and maximize total pressure recovery (thus saving weight while having high performance) by using a variation on Mach numbers around the designated speed for the Tornado, while using a mixed compression intake. Accordingly, a longer intake had better performance, but a shorter intake comes with lower weight. With lower speeds, a higher total pressure recovery and lower length is reached. This, along with the loss of importance of high speeds for most mission profiles, suggests that an aircraft with a lower top speed is advantageous as its weight lowers and performance increases.