Design of an academic unpowered axisymmetric scramjet for atmospheric captive flight at Mach number 4.18 using the training rocket FTI
Álvaro Francisco Santos Pivetta1; Giannino Ponchio Camillo2; Roberto da Cunha Follador2; Angelo Passaro2; Israel da Silveira Rêgo2; Marco Antonio Sala Minucci2; Paulo Gilberto de Paula Toro2
1 Instituto Tecnológico de Aeronáutica/ITA; 2 Instituto de Estudos Avançados/IEAv
doi:10.20906/CPS/CON-2016-1006
Resumo
An academic unpowered axisymmetric scramjet engine is been developed at the Instituto de Estudos Avançados, to perform atmospheric captive flight at 6.2 km of altitude with speed corresponding to Mach number 4.18. 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, just the operating speed of the scramjet, but, it is planned to have no combustion during the first atmospheric captive flight of the academic scramjet. In this present work will be used analytical and numerical methodologies to design the academic unpowered axisymmetric scramjet. Two-dimensional steady state, non-viscous, adiabatic compressible flow applied to the shock and expansion waves may be used as analytical theoretical analysis. The Fluent software may be applied for the numerical simulation considering non viscous calorically airflow for the academic unpowered axisymmetric scramjet. Implicit first order upwind spatial discretization is used to obtain the distributions of the thermodynamic properties and Mach number. Numerical simulation (static pressure, static temperature and static density) results at the inlet compression region are compared to the correspondent properties based on the analytical theoretical analysis.
Palavras-chave: scramjet; academic scramjet; training rocket; FTI