Application of hot-wire anemometry in shock-tube flows

Briassulis, G.; Honkan, A.; Andreopoulos, J.; Watkins, C. B.

doi:10.1007/bf00192230

Cited by 24 publications

(14 citation statements)

References 22 publications

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“…The first one is the constant mass flow during the whole aspiration phase. Later it will be found that the regime is exactly sonic, suggesting the existence of a critical mass flow as it exists for the similar case of a reservoir-nozzle system [30]. The second is the mass flux varies in a slower rate during the onset of the jet phase than during its offset, when it falls sharply, for both chosen frequencies.…”

Section: Mass Flux Outputmentioning

confidence: 81%

Experimental Measurement Benchmark for Compressible Fluidic Unsteady Jet

et al. 2018

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A benchmark of different measurement techniques is presented to characterize the dynamic response of a synthetic jet actuator working in compressible regime. The setup involves a piston-based synthetic jet, as well as the benchmarked measurements are hot-wire, cold-wire, Laser Doppler Anemometry, pressure transducer, and Schlieren visualization. Measured flow temperatures range from 20 °C to 150 °C, pressure ranges from 0.5 atm to 4 atm, and velocity are up to 300 m/s. The extreme values of these ranges are reached in an oscillating fashion at a frequency ranging from 30 to 100 Hz. The measurements are pointing out the limitation of cold-wire measurements, due to its high thermic inertia. The results show consistency in the velocity measurements, within 10% in the worst case, between all measurement techniques and the errors are traced back to the calibration ranges, whose sensitivity is also studied.

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Section: Mass Flux Outputmentioning

confidence: 81%

Experimental Measurement Benchmark for Compressible Fluidic Unsteady Jet

et al. 2018

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“…High-frequency pressure transducers, hotwire anemometry, and Rayleigh scattering techniques for ow visualization have been used in the present investigation. For more details on the hot-wire techniques applicable to shock tubes see Briassulis et al, 27 who also give estimates of uncertainties in the measurements.…”

Section: New Shock Tube Facilitymentioning

confidence: 99%

Interaction of Decaying Freestream Turbulence with a Moving Shock Wave: Pressure Field

Xanthos

Briassulis

Andreopoulos

2002

Journal of Propulsion and Power

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The unsteady interaction of a moving shock wave with nearly homogeneous and isotropic decaying compressible turbulence has been studied experimentally in a large-scale shock-tube facility by using rectangular grids of various sizes. The interaction has been investigated by measuring velocity, total pressure, and temperature inside the ow eld and static pressure at the wall of the shock tube with instrumentation of temporal and spatial resolution. Attenuation of the shock wave strength has been found to take place as a result of the interaction with the turbulent ow eld, which depends on the mesh size of the grid or its Reynolds number, the ow Mach number, and the initial Mach number of the shock wave. Finer grids produce turbulence, which attenuates the shock wave more than coarse grids at the same Mach number. Ampli cation of pressure uctuations after the interaction has been observed in all experiments, depending on grid size (initial turbulence level) and shock strength. Furthermore, this ampli cation is not the same through the whole range of wave numbers resolved.

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“…The present probe has been built upon the experience gained with vorticity measurements in incompressible flows 4 by using a probe with nine wires and with velocity measurements in compressible flows by using single and cross-wire probes. 9,22 The present vorticity probe, which consists of 12 wires, is a modification of the original design with nine wires. 4 The three additional wires were operated in the so-called constant current mode and used to measure time-dependent total temperature.…”

Section: Experimental Setup and Techniquesmentioning

confidence: 99%

Interaction of weakly compressible isotropic turbulence with planar expansion waves: Flow anisotropy and vorticity alignment

2010

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Further analysis of the experimental data of the velocity gradient tensor first published by Xanthos et al. ͓J. Fluid Mech. 584, 301 ͑2007͔͒ has been carried out and new results are reported here to provide additional insights on the effects of expansion waves interacting with isotropic turbulence. The flow field was generated by the reflection of an incoming shock wave at the open end of a large scale shock tube facility which interacted with the induced flow behind the incident shock wave which passed through a turbulence generating grid. In the present configuration the interaction is free from streamline curvature effects, which cause additional effects on turbulence. The strength of the applied expansive straining was 240 s −1 . Rectangular pattern grids of different mesh sizes were used to generate isotropic and homogeneous turbulence with turbulent Reynolds number Re based on Taylor's microscale between 450 and 488. Lateral vorticity fluctuations and fluctuations of enstrophy and all stretching vector components are drastically reduced during the interaction. Residual attenuation in the postinteraction flow field was found only in the lateral vorticity fluctuations and in the longitudinal stretching term S 11 ⍀ 1 . Helicity and the helicity angle were computed from the data and the orientation angle of the vorticity vector in reference to the velocity vector was determined. Large fluctuations of the helicity angle were observed which extend from 0°t o 180°with most probable values close to 30°and 130°and a mean value of 85°. Rotational dissipation rate was found to be high at these angles. The time-dependent signals of enstrophy, vortex stretching/tilting vector, and dissipation rate were found to exhibit a rather strong intermittent behavior which is characterized by high amplitude bursts followed by low level activities. It was found that the observed strong dissipative events are mostly associated with strong activities in the longitudinal stretching S 11 ⍀ 1 rather than with events in the lateral components.

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Application of hot-wire anemometry in shock-tube flows

Cited by 24 publications

References 22 publications

Experimental Measurement Benchmark for Compressible Fluidic Unsteady Jet

Experimental Measurement Benchmark for Compressible Fluidic Unsteady Jet

Interaction of Decaying Freestream Turbulence with a Moving Shock Wave: Pressure Field

Interaction of weakly compressible isotropic turbulence with planar expansion waves: Flow anisotropy and vorticity alignment

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