Eventos Anais de eventos
ENCIT 2018
Brazilian Congress of Thermal Sciences and Engineering
NUMERICAL ANALYSIS OF A GENERIC SCRAMJET AIR INLET
Submission Author:
Jonatha Wallace da Silva Araújo , RN
Co-Authors:
Paulo Toro, Jonatha Wallace da Silva Araújo, Emanuel Mendes, Sandi Souza, Israel Rêgo
Presenter: Jonatha Wallace da Silva Araújo
doi://10.26678/ABCM.ENCIT2018.CIT18-0107
Abstract
A generic hypersonic airbreathing propulsion based on supersonic combustion ramjet (scramjet) technology has been designed, at the Universidade Federal do Rio Grande do Norte (UFRN), using both analytical and numerical theoretical analysis. The scramjet will demonstrate supersonic combustion during Earth’s atmospheric free-flight at 30 km of geometric altitude and Mach number 6.8. Plane oblique shock wave (two-dimensional steady state, non-viscous, adiabatic calorically compressible airflow) is used for analytical theoretical analysis. Fluent software has been applied for the (Computational Fluid Dynamics) numerical simulation considering non-viscous calorically airflow for the scramjet inlet. Implicit second order upwind spatial discretization is used to obtain the contour plots of the static pressure, temperature, density and airflow velocity (and corresponding Mach number). Numerical simulation of the above quantities at the scramjet inlet are compared to the analytical theoretical results based on the plane oblique shock wave theory.
Keywords
Scramjet, supersonic combustion ramjet, hypersonic airbreathing propulsion, Numerical simulation
