Análise do regime de escoamento hipersônico através de bocais do tipo convergente-divergente

Abstract

The interest in simulation of regime flows at high speed, has become more present in recent decades, consequent to the increasing study in aerodynamics and the beginning of the Space Age. In the case of ascent or atmospheric reentry vehicles, such bodies are subjected to a hypersonic flow, whose Number of Mach, M, is greater or equal to 5. In such flow, two important phenomena occur, being the viscous interaction and the relation of high temperatures, between the body and the shock wave. This will cause, from a certain point, the gas to begin to undergo chemical reactions, as this will be under the effect of high temperatures. Consequently, it is provided that the isentropic expansion exponent, γ, is no longer constant due to the occurrence of gas dissociation. The use of CFD (Computational Fluid Dynamic) codes is an example of an essential element for the modeling of this type of flow. Such an approach is based on approximate (numerical) solutions of governing equations over a discrete mesh, which the more refined its numerical solution tends to be. The present work aims at numerically investigating this hypersonic flow, through a theoretical development, to obtain the convergent-divergent type nozzle geometry, using a MATLAB simulation.