Eventos Anais de eventos
ENCIT 2018
Brazilian Congress of Thermal Sciences and Engineering
DESIGN OF AN ACADEMIC SCRAMJET FOR ATMOSPHERIC CAPTIVE FLIGHT AT MACH NUMBER 4.18 COUPLED TO A ROCKET FTI
Submission Author:
Marcos Vinícius Sabino Pereira , RN
Co-Authors:
Paulo Toro, Marcos Vinícius Sabino Pereira, Jonatha Wallace da Silva Araújo, George Marinho, Gilvan Borba, João Felipe De Araujo Martos, Israel Rêgo
Presenter: Jonatha Wallace da Silva Araújo
doi://10.26678/ABCM.ENCIT2018.CIT18-0072
Abstract
An (academic) planar symmetric scramjet is being developed (by a Undergraduate Students) at the Universidade Federal do Rio Grande do Norte/UFRN, to perform atmospheric captive flight in high supersonic speed corresponding to Mach number 4.18, at 6.2 km of altitude. The academic scramjet will be launched by the Foguete de Treinamento Intermediário/FTI released from the Brazilian Launch Centers of Barreira do Inferno (CLBI) or of Alcântara (CLA). The Brazilian Launch Centers CLBI and CLA are the only national institutions that have the proper infrastructure (control center, payload-rocket integration lab, launch platform and tracking radars) and expertise in performing the launch of scramjet demonstrators. The FTI is used by CLBI and CLA for training of local operational teams. The FTI reaches speed close to Mach number 4 at 6.2 km of altitude, just the operating speed of the scramjet. It will have no combustion during the firsts atmospheric captive flight of the academic scramjet. Analytical methodology is used to design the academic planar symmetric scramjet. One-dimensional compressible flow (shock wave) theory, one-dimensional flow with heat addition and the one-dimensional compressible flow (expansion wave) theory coupled to the area ratio are applied to design the compression, combustor and expansion sections of the academic scramjet, respectively, considering no effects of boundary layer and calorically perfect gas airflow. For a given design conditions of any scramjet flying at high Mach number in the Earth’s dense atmospheric the presented methodology in this work is capable of evaluating the thermodynamic properties and Mach numbers (corresponding to flow velocities) from the leading-edge to trailing-edge of an airframe-integrated scramjet.
Keywords
Scramjet, supersonic combustion ramjet, hypersonic airbreathing propulsion
