Laser-Supported Directed-Energy "Air Spike" in Hypersonic Flow

Minucci, M. A. S.; Toro, Paulo; Oliveira, Antônio Carlos de; Ramos, Antonio G.; Chanes, J. B.; Pereira, A. L.; Nagamatsu, H. T.; Myrabo, Leik N.

doi:10.2514/1.2676

Cited by 18 publications

(14 citation statements)

References 14 publications

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“…There have also been studies done with plasma flow control in high-speed applications [11,14,15,16,17,18,19,20,21] . Plasma was generated in numerous ways including DC, AC, RF, microwave, arc, corona, and spark electric discharges, as well as laser induced breakdown, and applied to subsonic and supersonic flow regimes.…”

Section: Introductionmentioning

confidence: 98%

Transient Plasma Impact on Spectra of Flow Disturbances in a Corner Separation Zone at Mach 4.5

Houpt

Hedlund

Gordeyev

et al. 2016

47th AIAA Plasmadynamics and Lasers Conference

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This work was performed to study the effect on flow disturbances in the corner separation zone of a compression surface with a hypersonic boundary layer caused by a weakly ionized transient plasma generated upstream. Schlieren imaging was used to distinguish the corner separation zone for 15°, 20°, and 25° compression ramps at Mach 4.5 (nozzle exit). A Shack-Hartmann wavefront sensor was used to determine the dominant frequencies of flow oscillations at different locations in the flow field and the resulting effect of repetitively pulsed plasma actuators. A significant rise in amplitudes of high-frequency (>80 kHz) flow perturbations was found when pulsing the plasma at a frequency (100 kHz) higher than the natural dominant frequency of the boundary layer (~65 kHz). The plasma effect was negligible when operated below this frequency (50 kHz). PCB pressure sensors were used to determine the dominant frequencies of pressure oscillations present at the surface on the flat plate and compression ramp inside the separation zone. This technique can potentially be used for active control of the boundary layer condition and supersonic flow structure on the compression surface.

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Section: Introductionmentioning

confidence: 98%

Transient Plasma Impact on Spectra of Flow Disturbances in a Corner Separation Zone at Mach 4.5

Houpt

Hedlund

Gordeyev

et al. 2016

47th AIAA Plasmadynamics and Lasers Conference

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show abstract

“…The experimental investigations were conducted at Mach 5 freestream flow with unit Reynolds numbers of 11.0 × 10 6 , 13.0 × 10 6 , and 14.6 × 10 6 m - 1 Figure 1 shows the flow structure over the flat plate without laser energy addition. A leading shock wave (LSW) generated from the leading edge of the flat plate is slightly curved in the vicinity of the leading edge due to viscus interaction.…”

Section: Methodsmentioning

confidence: 99%

“…Laser energy deposition is an emerging technique to improve the aerodynamic performance of highspeed vehicles, and it has potential for various applications such as drag reduction [1,2], shock wave modification [3,4], and a controllable perturbation device for boundary layer transition studies [5].…”

Section: Introductionmentioning

confidence: 99%

Flow structure generated by laser-induced blast wave propagation through the boundary layer of a flat plate

Ukai

Kontis

Yang

2018

Aerospace Science and Technology

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Laser energy deposition generates localised flow structures that can be used as flow control devices in high-speed flows. In the present study, the interaction between a laser-induced blast wave and an incoming laminar boundary layer on a flat plate was experimentally investigated at a Mach 5 flow with three different unit Reynolds numbers. A hemispherical laser-induced blast wave (LIBW) is induced by focusing a 532 nm pulsed Nd:YAG laser beam on the surface of the plate. The hemispherical shaped fore wave front of the LIBW is locally transformed to an oblique shape, which results in a laser-induced oblique shock wave (LIOSW). As LIOSW propagates through the laminar boundary layer increases its thickness. With laser energy deposition near the leading edge of the flat plate, the LIOSW interacts and influences the leading edge shock wave (LSW). This interaction could contribute to the modulation of the LSW in scramjet intakes. A weak shock limb generated at the shape transition point of the LIBW or thermal spot due to laser-induced gas breakdown causes the boundary layer perturbation. The geometrical pattern produced due to the interaction between the LIOSW and the disturbed boundary layer remains similar to itself as it grows with time as well as at different local Reynolds numbers, 2.2 × 10 5 to 5.7 × 10 5 .

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“…Another group of plasma-related studies is focused on high-speed applications [12][13][14][15][16][17]. Various methods of plasma generation, including DC, AC, RF, microwave, arc, corona, and spark electric discharges, as well as laser-induced breakdown, have been used to modify both subsonic and supersonic flow fields.…”

Section: Introduction / Motivationmentioning

confidence: 99%

Control of Hypersonic BL Transition by Electrical Discharge (feasibility study)

Leonov¹,

Falempin²

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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This paper presents experimental data characterizing the microsecond-scale electric discharge in hypersonic airflow. The tests are performed to prove the feasibility of such a discharge application to control the boundary layer (BL) at low static pressures in terms of transition and separation. Discharge developments are analyzed using electrical measurements, synchronized gate camera imaging, and a schlieren visualization. The results demonstrate that a shallow-cavity plasma actuator may be used for the BL tripping with a frequency F>100kHz even at static pressure Pst<5Torr.

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Laser-Supported Directed-Energy "Air Spike" in Hypersonic Flow

Cited by 18 publications

References 14 publications

Transient Plasma Impact on Spectra of Flow Disturbances in a Corner Separation Zone at Mach 4.5

Transient Plasma Impact on Spectra of Flow Disturbances in a Corner Separation Zone at Mach 4.5

Flow structure generated by laser-induced blast wave propagation through the boundary layer of a flat plate

Control of Hypersonic BL Transition by Electrical Discharge (feasibility study)

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