EXPERIMENTAL INVESTIGATION OF THE BRAZILIAN 14-X B HYPERSONIC SCRAMJET AEROSPACE VEHICLE
João Felipe de Araujo Martos1; Renan Guilherme Santos Vilela1; Bruno Coelho Lima1; Sérgio Nicholas Pachon Laiton1; Thiago Victor Cordeiro Marcos2; Israel da Silveira Rego3; Paulo Gilberto de Paula Toro3
1 Instituto Tecnológico da Aeronáutica - ITA; 2 Fundação de Ciência, Aplicações e Tecnologia Espaciais - FUNCATE; 3 Instituto de Estudos Avançados - IEAv
doi:10.20906/CPS/CON-2016-1150
Resumo
The Brazilian hypersonic scramjet aerospace vehicle 14-X B is a technological demonstrator of a hypersonic airbreathing propulsion system based on the supersonic combustion (scramjet) intended to fly into the Earth's atmosphere at 30 km altitude and Mach number 7. The 14-X B was designed o the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonic of the Institute for Advanced Studies (IEAv). Hypersonic wind tunnels are one of the most important ground-based experimental facilities intended to simulate the flight conditions providing experimental data to design hypersonic aerospace vehicles and engines. The IEAv 0.60-m nozzle exit diameter Hypersonic Reflected Shock Tunnel named T3 and funded by São Paulo Research Foundation (FAPESP), was designed as a research & development facility for basic investigations in supersonic combustion. The T3 Hypersonic Shock Tunnel is a shock tube equipped with a convergent-divergent nozzle to produce high Mach number and high enthalpy flows in the test section close to those encountered during the flight of a aerospace vehicle into the Earth's atmosphere at hypersonic flight speeds. A 1-m long stainless steel 14-X B model was instrumented with twenty-eight piezoelectric pressure transducers along its compression surface, combustion chamber and nozzle. It was experimentally investigated on the equilibrium interface operational mode of the T3 Hypersonic Shock Tunnel, yielding a freestream Mach number from 7 to 8. Static pressure measurements at the lower surface of the 14-X B as well as high speed schlieren photographs taken from the 5.5° leading edge and the 14.5° deflection compression ramp provide experimental data that was compared to the analytic theoretical analysis and computational fluid dynamics simulation, both applied to the design of the 14-X B. Some physical phenomena were observed such as chocked flow due to growth of boundary layer and interaction boundary layer and oblique shock between ramps of compression. Therefore, it became necessary some adju
Palavras-chave: 14 X-B; Scramjet; Hypersonic