Mach 5 bow shock control by a nanosecond pulse surface dielectric barrier discharge

Bow shock perturbations in a Mach 5 air flow, produced by low-temperature, nanosecond pulse, and surface dielectric barrier discharge (DBD), are detected by phase-locked schlieren imaging. A diffuse nanosecond pulse discharge is generated in a DBD plasma actuator on a surface of a cylinder model pla...

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Bibliographic Details
Published in:Physics of fluids (1994) 2011-06, Vol.23 (6), p.066101-066101-11
Main Authors: Nishihara, M., Takashima, K., Rich, J. W., Adamovich, I. V.
Format: Article
Language:English
Subjects:
70 PLASMA PHYSICS AND FUSION TECHNOLOGY
ACTUATORS
AIR FLOW
Compressible flows
shock and detonation phenomena
COMPRESSION
DIELECTRIC MATERIALS
ELECTRON TEMPERATURE
EMISSION SPECTRA
Exact sciences and technology
Flow control
Fluid dynamics
Fundamental areas of phenomenology (including applications)
HYPERSONIC FLOW
Instrumentation for fluid dynamics
INTERACTIONS
ION TEMPERATURE
MACH NUMBER
PERTURBATION THEORY
Physics
PLASMA
PLASMA DIAGNOSTICS
PLASMA PRODUCTION
PULSES
SHOCK WAVES
Shock-wave interactions and shock effects
STAGNATION
SURFACES
WIND TUNNELS
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Summary:Bow shock perturbations in a Mach 5 air flow, produced by low-temperature, nanosecond pulse, and surface dielectric barrier discharge (DBD), are detected by phase-locked schlieren imaging. A diffuse nanosecond pulse discharge is generated in a DBD plasma actuator on a surface of a cylinder model placed in air flow in a small scale blow-down supersonic wind tunnel. Discharge energy coupled to the actuator is 7.3-7.8 mJ/pulse. Plasma temperature inferred from nitrogen emission spectra is a few tens of degrees higher than flow stagnation temperature, T=340±30 K. Phase-locked Schlieren images are used to detect compression waves generated by individual nanosecond discharge pulses near the actuator surface. The compression wave propagates upstream toward the baseline bow shock standing in front of the cylinder model. Interaction of the compression wave and the bow shock causes its displacement in the upstream direction, increasing shock stand-off distance by up to 25%. The compression wave speed behind the bow shock and the perturbed bow shock velocity are inferred from the Schlieren images. The effect of compression waves generated by nanosecond discharge pulses on shock stand-off distance is demonstrated in a single-pulse regime (at pulse repetition rates of a few hundred Hz) and in a quasi-continuous mode (using a two-pulse sequence at a pulse repetition rate of 100 kHz). The results demonstrate feasibility of hypersonic flow control by low-temperature, repetitive nanosecond pulse discharges.
ISSN:1070-6631
1089-7666
DOI:10.1063/1.3599697