Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic airspace vehicle

Rolim, Tiago Cavalcanti; Toro, Paulo; Minucci, M. A. S.; Oliveira, Antônio de Carlos de; Follador, Roberto da Cunha

doi:10.5028/jatm.2011.03027510

Cited by 10 publications

(7 citation statements)

References 15 publications

(16 reference statements)

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“…Th e temperature of the leading edge is inversely proportional to the square root of its radius, in other words, the more aerodynamic the shape, the higher the temperature (Kontinos et al 2001). Flight trajectories having rapid acceleration to Mach 10 impose signifi cant heat fl uxes and mechanical stress associated with vibration (Rolim et al 2011;Van Wie et al 2004). For example, the temperatures at a blunt leading edge like the space shuttle orbiter are approximately 1650 °C.…”

Section: Introductionmentioning

confidence: 99%

Effect of ZrB2 Particle Size on Pressureless Sintering of ZrB2 - ß-Sic Composites

Rocha¹,

Sene²,

JULIANI

et al. 2019

J.Aerosp. Technol. Manag.

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Zirconium diboride is an ultra high temperature ceramic material that leads this emerging class of materials because of its distinct combination of properties, including high melting temperature (> 3000 °C) and the lowest theoretical density (6.09 g·cm-3) among the borides. This combination of properties makes ZrB2 candidate for airframe leading edges on sharp-bodied reentry vehicles. In this work, the effect of particle size of ZrB2 on the pressureless sintering of ZrB2-SiC composites was studied, using ZrB2 powder with average particle size of 2.6 and 14.2µm. Four different vol% concentration of ß-SiC (0, 10, 20 and 30 vol%) were added to as-received and planetary milled ZrB2 powder. Samples were pressureless sintered at 2050 °C/1h in argon atmosphere. The reduction of initial ZrB2 particle size led to composites with better results of densification, mechanical properties and oxidation resistance regardless ß-SiC addition, showing relative densities around 92.5 %Theoretical Density (Td) and flexural strength and microhardness around 260 MPa and 17.5 GPa, respectively. Composites processed with as-received ZrB2 powder showed increasing in densification and flexural strength with the SiC content increasing. Relative density varied from 74.7 to 90.8 %TD and flexural strength from 102 to 241 MPa, for 0 and 30 vol% of SiC, respectively.

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Section: Introductionmentioning

confidence: 99%

Effect of ZrB2 Particle Size on Pressureless Sintering of ZrB2 - ß-Sic Composites

Rocha¹,

Sene²,

JULIANI

et al. 2019

J.Aerosp. Technol. Manag.

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“…Later, Rolim added a compression and expansion ramps to the pure waverider surface in order to provide the flow on a scramjet engine. The 14.5° deflection compression ramp is designed to capture the entire air flow compressed by the 5.5° waverider leading edge and to provide the ideal conditions for the supersonic combustion of the hydrogen, while the expansion section is assumed a 15° ramp [1][2][3] . A 718.28-mm.…”

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

“…A 718.28-mm. 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 .…”

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

“…The schlieren photographs [1][2][3] , Figs. 19 and 20, take from the 5.5° waverider leading edge and the 14.5° deflection compression ramp (20° aligned with the upper surface) designed to capture the entire air flow compressed by the 5.5° waverider leading edge, provide enough experimental data to design the position of the combustion chamber of the 14-X Hypersonic Aerospace Vehicle.…”

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

See 1 more Smart Citation

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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“…Three hypersonic shock-tunnels (denoted T1, T2 and T3) are operating in Brazil at the IEAv near São Paulo [15]. These facilities are utilized for investigating scramjet [16] and aerothermodynamics related to Earth orbital entry [17,18] but are not used for radiation and chemical kinetics investigation, as a consequence they have not been detailed in this paper.…”

Section: Introductionmentioning

confidence: 99%

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

Reynier¹

2016

Progress in Aerospace Sciences

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Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic airspace vehicle

Cited by 10 publications

References 15 publications

Effect of ZrB2 Particle Size on Pressureless Sintering of ZrB2 - ß-Sic Composites

Effect of ZrB2 Particle Size on Pressureless Sintering of ZrB2 - ß-Sic Composites

Brazilian 14-X Hypersonic Aerospace Vehicle Project

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

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