Experimental Results of a Mach 10 Conical-Flow Derived Waverider

Rolim, Tiago Cavalcanti; António, Marco; Minucci, S.; Gilberto, Paulo; Toro, Paulo

doi:10.2514/6.2009-7433

Cited by 5 publications

(6 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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%

“…high combustion chamber [4][5][6]39 was integrated at the 14-X Hypersonic waverider Aerospace Vehicle lower surface, between the end of 14.5° deflection compression ramp and the beginning at 15° expansion ramp, Fig. 21, defined by the 14-X waverider aerodynamic experimental results [1][2][3] . Figure 21: The 14-X waverider scramjet Mach number 10 model main dimensions.…”

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

See 3 more Smart Citations

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

Self Cite

View full text Add to dashboard Cite

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.

show abstract

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

Section: -X Hypersonic Waverider Scramjet Aerospace Vehicle Expmentioning

confidence: 99%

See 2 more Smart Citations

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

Self Cite

View full text Add to dashboard Cite

show abstract

“…Wang (20) investigated design method for a cone-derived waverider at Mach 6 and its basic aerodynamic characteristics, especially the improvement of the configuration for a higher lift-to-drag ratio. Rolim (21) presented Mach 10 shock tunnel test results of an optimised waverider with sharp leading edge. This particular waverider was generated from a conical flowfield with the volumetric efficiency and the viscous L/D as optimisation parameters.…”

Section: Introductionmentioning

confidence: 99%

Modification impact on aerodynamic performance of hypersonic waverider

Chen¹,

Hou

Liu

et al. 2011

Aeronaut. j.

View full text Add to dashboard Cite

Waverider serves as a good candidate for hypersonic vehicles. The typical waverider has sharp leading edge and no control face, which is inappropriate for practical use. This paper puts forward a method modifying the waverider, and the modification impact on the performance of waverider at hypersonic flow conditions is studied. The modification is based on blunted waverider, includes cutting the tip and introducing two control wings. The modification’s effect on aerodynamic performance is obtained and analysed through Computational Fluid Dynamics (CFD) techniques. When blunted with 2cm radius, the waverider retains its good aerodynamic performance and the heat flux at the stagnation point can be managed. Three factors of the introduced wing are argued, the fixed angle, aspect ratio and wing area. Results show that influence on the aerodynamic coefficient is slight and the vehicle retains its high lift-to-drag ratio. The main influences of the modification are the control ability and trim efficiency, which is the motivation of this work and can be adapted when designing a practical waverider.

show abstract