Flow Characterization of the T3 Hypersonic Shock Tunnel

Pinto, David Romanelli; Marcos, Thiago Victor Cordeiro; Galvão, Victor Alves Barros; Oliveira, Antônio Carlos de; Chanes, J. B.; Minucci, M. A. S.; Toro, Paulo

doi:10.1007/978-3-642-25688-2_84

Cited by 3 publications

(2 citation statements)

References 5 publications

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“…The simplest Reflected 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 atmospheric flight of the 14-X B at hypervelocity. The basic hypersonic shock tunnel consists of a high-pressure section (driver) and a low-pressure section (driven) separated from each other by a double diaphragm system (DDS), a convergent-divergent nozzle and its diaphragm (placed at the end of the driven section), and a test section terminated by a large dump tank [15]. 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.…”

Section: Experimental Apparatusmentioning

confidence: 99%

Experimental Investigation of Brazilian 14-X B Hypersonic Scramjet Aerospace Vehicle

Martos

Rêgo²,

Laiton

et al. 2017

International Journal of Aerospace Engineering

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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.

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Section: Experimental Apparatusmentioning

confidence: 99%

Experimental Investigation of Brazilian 14-X B Hypersonic Scramjet Aerospace Vehicle

Martos

Rêgo²,

Laiton

et al. 2017

International Journal of Aerospace Engineering

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“…long stainless steel "waverider" model [1][2][3][4][5][6] , Fig. 18, instrumented with seven piezoelectric pressure transducers on the compression surface, was experimentally investigated on the equilibrium interface mode operation at the T3 0.60-m. nozzle exit diameter Hypersonic Shock Tunnel T3 [37][38] at freestream Mach number from 8.9 to 10 with stagnation pressures between 2176-2938 psi and temperatures at the range of 1558-2150 K 1-3 . Figure 18: Instrumented "waverider" model installed at T3 Hypersonic Shock Tunnel.…”

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

Brazilian 14-X Hypersonic Aerospace Vehicle Project

Toro¹,

Minucci²,

Rolim³

et al. 2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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The Brazilian 14-X Hypersonic Aerospace Vehicle, a new generation of scientific aerospace vehicle, designed at Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, at Institute for Advanced Studies (IEAv), is part of the continuing effort of the Department of Aerospace Science and Technology (DCTA), to develop a technological demonstrator using: i) waverider technology to provide lift to the aerospace vehicle, and ii) scramjet technology to provide hypersonic airbreathing propulsion system based on supersonic combustion. In consequence of the nature of the supersonic combustion engines, they are unable to produce thrust while stationary, the static thrust is zero. Accordingly, they must be accelerated to a speed such that the shock waves produced by the air intake are able to compress the atmospheric air. This velocity, called initial operation speed, is approximately four times the speed of sound, Mach 4, considering scramjet. Two-stage, unguided, rail launched, solid rocket engines will be used to accelerate the 14-X Hypersonic Aerospace Vehicle to the pre-established conditions to operate the scramjet engine, i.e., position (altitude, latitude and longitude), speed (Mach number), dynamic pressure and angle of attack. The 14-X Hypersonic Aerospace Vehicle project consists of four atmospheric flights. The first flight is planned for 14-X captive (accelerator and 14-X vehicles coupled during the entire flight) unpowered scramjet Mach number 6; the second for 14-X free (accelerator and 14-X vehicles separated after burn of 2 nd stage of accelerator vehicle) unpowered scramjet Mach number 6 flight; and the two last are planned for free hydrogen-powered scramjet Mach number 6 and Mach number 10, respectively. Pure waverider aerodynamic, scramjet power off and power on as well as 14-X stage separation will be experimentally investigated using the three Hypersonic Shock Tunnels at Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics. Pressure and temperature measurements at pure waverider external upper and lower surfaces and scramjet power off and power on internal surfaces will be obtain to provide wind-tunnel data to design the full 2-m. long atmospheric flight of 14-X Hypersonic waverider scramjet Aerospace Vehicle. Non-intrusive measurements using optical diagnostic techniques have been implemented at Hypersonic Shock Tunnels, as well as in-house computational fluid dynamics have been developed for waverider, scramjet and 14-X Hypersonic Aerospace Vehicle.

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