Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
MODELING, IMPLEMENTATION AND APPLICATION OF A TOOL FOR PRELIMINARY HYPERSONIC AIRBREATHING VEHICLE DESIGN
Submission Author:
Luiz Henrique Silva Marques Soares , SP
Co-Authors:
Luiz Henrique Silva Marques Soares, Pedro Paulo Batista de Araújo, Paulo Toro, João Felipe De Araujo Martos
Presenter: Luiz Henrique Silva Marques Soares
doi://10.26678/ABCM.COBEM2021.COB2021-0495
Abstract
In this work, a tool for preliminary hypersonic airbreathing vehicle design, using scramjet technology, was modeled, implemented, and applied. In the initial stages of the design of aeronautical and space systems, it is common to survey the requirements and needs of the project and, subsequently, to define preliminary configurations that can solve doubts, show the existence of problems and be the basis for future details of the systems. Thus, the evaluation of scramjet vehicle planar geometry was determined, and, to evaluate the aerodynamics of the vehicle, considering the hypothesis of perfect gas and inviscid flow, the model was sectioned into the inlet, combustion, and expansion sections applying the respective theoretical-analytical analyzes for each section. For the inlet, the application of the theory of oblique shock wave was considered, and to optimize the geometry, the maximum pressure recovery method was applied to minimize the loss of performance during compression. The combustion section was considered only as a union between the intake and the expansion sections, therefore, the flow with heat addition was disregarded. For the expansion section, the Prandtl-Meyer expansion wave theory was implemented to the point where it was applicable and, subsequently, the area ratio theory was used to finalize the expansion section. Subsequently, in order to verify the effectiveness of the tool, two scramjet vehicle geometries were developed, both for flight at 30 km of geometric altitude at the Mach numbers 7 and 10, respectively. Then, in order to compare results, both geometries were evaluated in computational fluid dynamics (CFD) simulations using the ANSYS Fluent code. In the end, with the convergence between analytical and numerical results, the applicability of the tool for preliminary hypersonic airbreathing vehicle design, using scramjet technology was demonstrated. In addition, the resulting differences in geometries were presented when the vehicles are developed for application at different speeds.
Keywords
Hypersonic, Airbreathing Propulsion, Scramjet, Oblique Shock Wave, Planar
