Eventos Anais de eventos
ENCIT 2018
Brazilian Congress of Thermal Sciences and Engineering
A NEW APPROACH TO OPTIMIZE THE SCRAMJET INLET DESIGN APPLYING THE TOTAL PRESSURE RECOVERY
Submission Author:
Alef Fernandes , RN
Co-Authors:
Paulo Toro, Alef Fernandes, George Marinho, Gilvan Borba, João Felipe De Araujo Martos, Israel Rêgo
Presenter: Alef Fernandes
doi://10.26678/ABCM.ENCIT2018.CIT18-0074
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 analytical theoretical analysis (engineering approach). Final paper will present a scramjet inlet design based on the condition of equal strength shocks and total pressure recovery. One-dimensional compressible flow (shock wave) theory, which may readily describe many features of compression region of the airbreathing engine, is used to estimate the shock wave angles, thermodynamic properties and the velocities (Mach number) of the hypersonic atmospheric air flow, at the generic scramjet inlet, needed to calculate the total pressure recovery. After a trade-off combination among total pressure recovery and a large number of ramps (which will tend to an isentropic compressor), an adequate number of compression ramps (oblique shockwaves) will be selected to match the desired flow properties on the combustion chamber, such as the atmospheric airflow with temperature, higher than the ignition temperature of hydrogen, at supersonic Mach number.
Keywords
Scramjet, supersonic combustion, hypersonic airbreathing propulsion
