Modelagem e implementação de ferramenta para projeto preliminar de motor hipersônico aspirado

Abstract

In this work, a tool for preliminary hypersonic airbreathing design, scramjet technology, is modeled and implemented. It was considered planar and axisymmetric geometries and the model was sectioned into inlet, combustor and expansion sections. For planar inlet, the oblique shock wave theory was used and, for axisymmetric inlet, the conical shock wave theory was adopted. Besides that, to avoid loss performance, the theory of total pressure recovery was considered. In combustor section, modeled equally for the two geometries, the theory of unidimensional flow with heat adition (Rayleigh Flow), was considered. In the expansion section, for planar geometry, the Prandtl-Meyer expansion waves and the area ratio theory were used. For axisymmetric geometry the spike nozzle was used. For more reallystic analisys, real gas was considered by adiabatic expansion coefficient variation in temperature function and the inlet boundary layer is determined. To tool efficiency verify, a geometries development to fly at geopotential altitude of 30 km in Mach number 7 was proposed. Then, the tool and the obtained results were validated with fluid dynamics simulation in Ansys Fluent software. At the end, considered that the objectives were achieved and noted the need to develop analytics, numerical and experimental methodologies to project scramjet engine.