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Self-excited compressible flow in a pipe-collar nozzle

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TLDR
In this paper, a pipe-collar flow was investigated using a simple device composed of a convergent nozzle and a pipe lengthened by a collar with an enlarged cross-section.
Abstract
The turbulent flow in a duct with an abrupt increase in its cross-sectional area is very unstable and exhibits strong oscillations. Such a flow is investigated experimentally using a simple device — a pipe–collar nozzle, composed of a convergent nozzle and a pipe lengthened by a collar with an enlarged cross-section. The oscillating flow characteristics are considered over a wide range of flow velocities including both subsonic and transonic flow regimes. Two modes of symmetric and one of asymmetric oscillations are distinguished. For the first mode of symmetric oscillation the jet is separated in each phase of the oscillation cycle, whereas for the second the jet alternately separates and reattaches to the collar wall. Both modes of symmetric oscillations are controlled by shear-layer instability of the collar flow. For low velocities and short collars the oscillation is also affected by the organ-pipe resonance in the preceding pipe. The asymmetric oscillation appears at relatively large flow Mach numbers. This mode exhibits a radial resonance of the jet.

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Citations
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Journal ArticleDOI

Mixing enhancement in supersonic free shear flows

TL;DR: In this article, the mixing augmentation methods employed efficiently in sub- sonic flows failed to work at elevated Mach numbers, and some were inefficient because they were utilized outside their effective range.
Journal ArticleDOI

Damping and reflection coefficient measurements for an open pipe at low Mach and low Helmholtz numbers

TL;DR: In this paper, the authors compared the results of Ronneberger and Ahrens (1977) with results of linear theory for the propagation of acoustic waves in a pipe with a quiescent fluid.
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Cavity-actuated supersonic mixing and combustion control

TL;DR: In this paper, a cavity-actuated forcing technique is demonstrated for increasing the spreading rate of compressible shear layers in a Mach 2.0 air jet with a convective Mach number (M c ) of 0.85.
Journal ArticleDOI

Review of combustion stabilization for hypersonic airbreathing propulsion

TL;DR: A review of fundamental research in combustion stabilization for hypersonic airbreathing propulsion is presented in this paper, which outlines both experimental and numerical research progress made towards combustion stabilization over the entire hypheratic regime, and intended to lay the groundwork for further studies which can provide optimized design guidelines for the next generation of high-speed air-to-air propulsion systems.

Aeroacoustic sources in internal flows

TL;DR: In this article, a theory is developed which describes the sound generated by aerodynamic sources, in particular the theory underlying the vortex sound phenomenon, in which the source of vortex sound is unsteady vorticity, interacting with an acoustic field.
References
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Journal ArticleDOI

Dynamics of an impinging jet. Part 1. The feedback phenomenon

TL;DR: In this paper, the authors show that a feedback mechanism is responsible for the sudden change observed in the pressure fluctuations at the onset of resonance in a high-speed subsonic jet impinging on a flat plate.
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On the three families of instability waves of high-speed jets

TL;DR: In this article, an analytical and computational study of the normal-mode small-amplitude waves of high-speed jets is presented, and three families of instability waves have been identified: (1) the familiar Kelvin-Helmholtz instability waves, (2) supersonic instability waves; and (3) subsonic waves.
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The self-excited axisymmetric jet

TL;DR: In this article, a large-scale coherent structure in the circular jet is considered, taking into account the advantages of inducing controlled perturbation through self-sustained excitation with the whistler nozzle.
Journal ArticleDOI

The 'whistler-nozzle' phenomenon

TL;DR: In this paper, it was shown that the whistler self-excitation results from coupling of two independent resonance mechanisms: shear-layer tone resulting from the impingement of pipe-exit shear layer on the collar lip, and organ-pipe resonance of the pipe-nozzle.
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