Abstract
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) to be tested in flight into the Earth’s atmosphere at an altitude of 30 km and Mach number 7. The 14-X B has been designed at the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, Institute for Advanced Studies (IEAv), Brazil. The IEAv T3 Hypersonic Shock Tunnel is a ground-test facility able to produce high Mach number and high enthalpy flows in the test section close to those encountered during the flight of the 14-X B into the Earth’s atmosphere at hypersonic flight speeds. A 1 m long stainless steel 14-X B model was experimentally investigated at T3 Hypersonic Shock Tunnel, for freestream Mach numbers ranging from 7 to 8. Static pressure measurements along 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, provided experimental data. Experimental data was compared to the analytical theoretical solutions and the computational fluid dynamics (CFD) simulations, showing good qualitative agreement and in consequence demonstrating the importance of these methods in the project of the 14-X B hypersonic scramjet aerospace vehicle.
Highlights
A new era of hypersonic flight started, in August 1963, when Robert M
The T3 Hypersonic Shock Tunnel was designed [14] to be operated in the 6–25 flight Mach number range, generating reservoir enthalpies in excess of 10 MJ/kg and reservoir pressures up to 25 MPa when operated in the equilibriuminterface mode, with estimated useful test time up to 10 ms
A 1 m long stainless steel 14-X B model (Figure 7(a)) instrumented with twenty-nine piezoelectric pressure transducers on its lower surface was experimentally investigated in the T3 Hypersonic Shock Tunnel running at freestream Mach numbers from 7 to 8 and in the equilibrium-interface mode operation
Summary
A new era of hypersonic flight started, in August 1963, when Robert M. Theoretical calculations and computational fluid dynamics simulations of such an internal airflow are presented
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