Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
DEVELOPMENT AND COMPARISON OF PLANAR AND CONICAL SCRAMJET VEHICLE INLET
Submission Author:
Luiz Henrique Silva Marques Soares , SP
Co-Authors:
Luiz Henrique Silva Marques Soares, Heidi Korzenowski, Paulo Toro, João Felipe De Araujo Martos
Presenter: Luiz Henrique Silva Marques Soares
doi://10.26678/ABCM.COBEM2021.COB2021-0497
Abstract
This work presents the development and comparison of planar and conical configurations for the compression section of a hypersonic airbreathing vehicle, using scramjet technology. The analysis of different configurations in the initial stages of the design of scramjet vehicles is necessary to determine the most suitable one to be applied based on the requirements of the project. Thus, the evaluation of the planar and conical inlets was considered to compare the influence of the choice of configuration on the performance and dimensions of the scramjet vehicles inlet. In order to perform a conservative analysis, the hypothesis of perfect gas and inviscid flow was considered, applying the theoretical-analytical and numerical analyzes, respectively, for each configuration. For the planar inlet, the theory of planar oblique shock waves was applied. As for the conical inlet, the theory of conical oblique shock waves was applied using the Taylor-Maccoll solution with the necessary adaptations for application in more than one subsequent cone. In order to optimize geometries and minimize performance losses during compression, the maximum pressure recovery method was applied. Subsequently, a case study was proposed considering the Mach number 7 and 30 km of geometric altitude, of which a model for each configuration was developed. Then, were evaluated in computational fluid dynamic (CFD) simulations using the ANSYS Fluent code in order to compare with the analytical results. In the end, it was verified the applicability of the formulation for the definition of scramjet vehicles inlet, with the convergence between the analytical and numerical results. Subsequently, the results obtained were presented in a comparative manner, highlighting the dimensional and performance differences that the variation in geometry causes. Thus, the importance of evaluating the different geometries that can be applied in the scramjet inlets was emphasized.
Keywords
Hypersonic, Airbreathing Propulsion, Scramjet, Oblique Shock Wave, Conical Shock Wave
