Instabilities in the slit-jet flow field

1983 ◽  
Vol 132 ◽  
pp. 79-86 ◽  
Author(s):  
J. F. Foss ◽  
D. Korschelt
Keyword(s):  
Reynolds Number ◽  
Flow Field ◽  
Large Scale ◽  
Jet Flow ◽  
Instability Mode ◽  
Regular Pattern ◽  
Additional Information ◽  
The Third ◽  
Second Mode ◽  
Convection Speed

Three modes of instabilities in the slit-jet flow field are recognized. Additional evidence for the universality of the Strouhal number for the second mode ST = fw/U0 ≈ 0.43 and additional information on the wavelength (λ) between, and convection speed uc of the symmetrically placed, large-scale motions that result from this instability are presented. Specifically λ/w ≈ 1.2 and uc/U0 ≈ 0.51. The third instability mode is initiated at a Reynolds number U0w/v of approximately 1600; this instability results in a loss of the regular pattern associated with the large-scale motions.

Modeling Wave Attenuation With Rigid Vegetation Plants

2014 ◽  
Author(s):  
Don Liu ◽  
Yonglai Zheng
Keyword(s):  
High Resolution ◽  
Flow Field ◽  
Coastal Wetlands ◽  
Large Scale ◽  
High Efficiency ◽  
Wave Attenuation ◽  
Direct Numerical Simulations ◽  
Regular Pattern ◽  
Rigid Vegetation ◽  
Cylinder Model

Virtual Cylinder Model (VCM) was used to simulate flows over vegetation plants (cylinders) in coastal wetlands. VCM is capable of characterizing the flow field with a few plants as well as numerous plants with high efficiency and accuracy. Numerical results of flow over cylinders at a regular pattern are compared with Direct Numerical Simulations and at irregular patterns are presented with varied resolutions. VCM provides decent accuracy and efficiency without high resolution in tiny mesh. Results demonstrate that it is suitable for large-scale simulation of vegetation resilience to protect coastal wetlands from waves.

scholarly journals Reynolds number and wind tunnel wall effects on the flow field around a generic UHBR engine high-lift configuration

2020 ◽  
Vol 11 (4) ◽  
pp. 1009-1023 ◽  
Author(s):  
Junaid Ullah ◽  
Aleš Prachař ◽  
Miroslav Šmíd ◽  
Avraham Seifert ◽  
Vitaly Soudakov ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Flow Field ◽  
Test Section ◽  
Large Scale ◽  
Scale Model ◽  
Small Scale ◽  
Wall Effects ◽  
Tunnel Wall ◽  
High Lift

Abstract RANS simulations of a generic ultra-high bypass ratio engine high-lift configuration were conducted in three different environments. The purpose of this study is to assess small scale tests in an atmospheric closed test section wind tunnel regarding transferability to large scale tests in an open-jet wind tunnel. Special emphasis was placed on the flow field in the separation prone region downstream from the extended slat cut-out. Validation with wind tunnel test data shows an adequate agreement with CFD results. The cross-comparison of the three sets of simulations allowed to identify the effects of the Reynolds number and the wind tunnel walls on the flow field separately. The simulations reveal significant blockage effects and corner flow separation induced by the test section walls. By comparison, the Reynolds number effects are negligible. A decrease of the incidence angle for the small scale model allows to successfully reproduce the flow field of the large scale model despite severe wind tunnel wall effects.

scholarly journals Performance of distributed multiscale simulations

2014 ◽  
Vol 372 (2021) ◽  
pp. 20130407 ◽  
Author(s):  
J. Borgdorff ◽  
M. Ben Belgacem ◽  
C. Bona-Casas ◽  
L. Fazendeiro ◽  
D. Groen ◽  
...  
Keyword(s):  
Load Distribution ◽  
Large Scale ◽  
Multiscale Simulations ◽  
Distributed Resources ◽  
Multiple Resources ◽  
The Third ◽  
Simulation Speed ◽  
Local Resources ◽  
Second Mode ◽  
Different Characteristics

Multiscale simulations model phenomena across natural scales using monolithic or component-based code, running on local or distributed resources. In this work, we investigate the performance of distributed multiscale computing of component-based models, guided by six multiscale applications with different characteristics and from several disciplines. Three modes of distributed multiscale computing are identified: supplementing local dependencies with large-scale resources, load distribution over multiple resources, and load balancing of small- and large-scale resources. We find that the first mode has the apparent benefit of increasing simulation speed, and the second mode can increase simulation speed if local resources are limited. Depending on resource reservation and model coupling topology, the third mode may result in a reduction of resource consumption.

Higher-order flow modes in turbulent Rayleigh–Bénard convection

2016 ◽  
Vol 805 ◽  
pp. 31-51 ◽  
Author(s):  
Heng-Dong Xi ◽  
Yi-Bao Zhang ◽  
Jian-Tao Hao ◽  
Ke-Qing Xia
Keyword(s):  
Large Scale ◽  
Experimental Studies ◽  
Higher Order ◽  
Working Fluid ◽  
Dynamical Process ◽  
Total Flow ◽  
Flow Energy ◽  
The Third ◽  
Higher Order Modes ◽  
Second Mode

We present experimental studies of higher-order modes of the flow in turbulent thermal convection in cells of aspect ratio ($\unicode[STIX]{x1D6E4}$) 1 and 0.5. The working fluid is water with the Prandtl number ($Pr$) kept at around 5.0. The Rayleigh number ($Ra$) ranges from $9\times 10^{8}$ to $6\times 10^{9}$ for $\unicode[STIX]{x1D6E4}=1$ and from $1.6\times 10^{10}$ to $7.2\times 10^{10}$ for $\unicode[STIX]{x1D6E4}=0.5$. We found that in $\unicode[STIX]{x1D6E4}=1$ cells, the first mode, which corresponds to the large-scale circulation (LSC), dominates the flow. The second mode (quadrupole mode), the third mode (sextupole mode) and the fourth mode (octupole mode) are very weak, on average these higher-order modes each contains less than 4 % of the total flow energy. In $\unicode[STIX]{x1D6E4}=0.5$ cells, the first mode is still the strongest but less dominant, the second mode becomes stronger which contains 13.7 % of the total flow energy and the third and the fourth modes are also stronger (containing 6.5 % and 1.1 % of the total flow energy respectively). It is found that during a reversal/cessation, the amplitude of the second mode and the remaining modes experiences a rapid increase followed by a decrease, which is opposite to the behaviour of the amplitude of the first mode – it decreases to almost zero then rebounds. In addition, it is found that during the cessation (reversal) of the LSC, the second mode dominates, containing 51.3 % (50.1 %) of the total flow energy, which reveals that the commonly called cessation event is not the cessation of the entire flow but only the cessation of the first mode (LSC). The experiment reveals that the second mode and the remaining higher-order modes play important roles in the dynamical process of the reversal/cessation of the LSC. We also show direct evidence that the first mode is more efficient for heat transfer. Furthermore, our study reveals that, during the cessation/reversal of the LSC, $Nu$ drops to its local minimum and the minimum of $Nu$ is ahead of the minimum of the amplitude of the LSC; and reversals can be distinguished from cessations in terms of global heat transport. A direct velocity measurement reveals the flow structure of the first- and higher-order modes.

scholarly journals An Investigation of Factors Influencing the Calibration of 5-Hole Probes for 3-D Flow Measurements

1992 ◽  
Author(s):  
R. G. Dominy ◽  
H. P. Hodson
Keyword(s):  
Reynolds Number ◽  
Large Scale ◽  
Reynolds Numbers ◽  
General Behaviour ◽  
Flow Measurements ◽  
Low Reynolds Numbers ◽  
Additional Information ◽  
Reynolds Number Effects ◽  
Low Speed Wind Tunnel ◽  
Probe Head

The effects of Reynolds number, Mach number and turbulence on the calibrations of commonly used types of 5-hole probe are discussed. The majority of the probes were calibrated at the exit from a transonic nozzle over a range of Reynolds numbers (7×103 < 80×103 based an probe tip diameter) at subsonic and transonic Mach numbers. Additional information relating to the flow structure were obtained from a large scale, low speed wind tunnel. The results confirmed the existence of two distinct Reynolds number effects. Flow separation around the probe head affects the calibrations at relatively low Reynolds numbers while changes in the detailed structure of the flow around the sensing holes affects the calibrations even when the probe is nulled. Compressibility is shown to have little influence upon the general behaviour of these probes in terms of Reynolds number sensitivity but turbulence can effect the reliability of probe calibrations at typical test Reynolds numbers.

On the noise sources of the unsuppressed high-speed jet

1971 ◽  
Vol 50 (1) ◽  
pp. 21-31 ◽  
Author(s):  
K. A. Bishop ◽  
J. E. Ffowcs Williams ◽  
W. Smith
Keyword(s):  
Reynolds Number ◽  
High Speed ◽  
Large Scale ◽  
Jet Noise ◽  
Jet Flow ◽  
Scale Model ◽  
Small Scale ◽  
Noise Sources ◽  
Supersonic Transport ◽  
Scale Turbulence

The paper describes an interpretation of jet-noise theory and scale-model experiments to highlight physical properties of jet-noise sources at very high speed. The study is prompted by current efforts to suppress the noise of supersonic transport aircraft.The principal noise sources are shown to be very large-scale wave-like undulations of the jet flow that travel downstream at supersonic speed for a distance of several jet diameters. These motions are relatively well ordered and are probably more akin to recognizable instabilities of a laminar flow than the confused small-scale turbulence. Because of this we postulate a model of the noise generating motions as the instability products of a jet flow of low equivalent Reynolds number. This Reynolds number is based on an eddy viscosity and can be further reduced by artificially increasing the small-scale turbulence level. This step would tend to stabilize the flow and inhibit the formation of large-scale noise producing eddies.

An Investigation of Factors Influencing the Calibration of Five-Hole Probes for Three-Dimensional Flow Measurements

1993 ◽  
Vol 115 (3) ◽  
pp. 513-519 ◽  
Author(s):  
R. G. Dominy ◽  
H. P. Hodson
Keyword(s):  
Reynolds Number ◽  
Large Scale ◽  
Three Dimensional ◽  
Reynolds Numbers ◽  
Flow Measurements ◽  
Low Reynolds Numbers ◽  
Additional Information ◽  
Reynolds Number Effects ◽  
Low Speed Wind Tunnel ◽  
Probe Head

The effects of Reynolds number, Mach number, and turbulence on the calibrations of commonly used types of five-hole probe are discussed. The majority of the probes were calibrated at the exit from a transonic nozzle over a range of Reynolds numbers (7 × 103 < Re < 80 × 103 based on probe tip diameter) at subsonic and transonic Mach numbers. Additional information relating to the flow structure were obtained from a large-scale, low-speed wind tunnel. The results confirmed the existence of two distinct Reynolds number effects. Flow separation around the probe head affects the calibrations at relatively low Reynolds numbers while changes in the detailed structure of the flow around the sensing holes affects the calibrations even when the probe is nulled. Compressibility is shown to have little influence upon the general behavior of these probes in terms of Reynolds number sensitivity but turbulence can affect the reliability of probe calibrations at typical test Reynolds numbers.

A study of a conductive laminar jet flow in an applied magnetic field

SIMULATION ◽  
2019 ◽  
Vol 95 (10) ◽  
pp. 995-1011
Author(s):  
Cheng-Hsing Hsu ◽  
Te-Hui Tsai ◽  
Ching-Chuan Chang ◽  
Yi Chen
Keyword(s):  
Magnetic Field ◽  
Reynolds Number ◽  
Flow Field ◽  
Applied Magnetic Field ◽  
Recirculation Zone ◽  
Hartmann Number ◽  
Control Volume ◽  
Jet Flow ◽  
Channel Width ◽  
Laminar Jet

This study investigates steady two-dimensional laminar confined jet flow in the presence of an applied magnetic field. The magnetohydrodynamic equations with the format of the stream function and vorticity formulation of the fluid flow are solved numerically. A numerical method was developed by using a first-order upwind scheme at the boundaries and a second-order finite control volume scheme in the flow field. The results show that the expansion region of the jet is moving downstream while the channel width and the Reynolds number are increasing. The vortex and the recirculation zone are stretched with increased Hartmann number, and the jet expansion region is moving upstream while the vortex and the recirculation zone are reduced. The channel width and the Reynolds number for the jet development are positive efforts and the Hartmann number has a suppressed effect in the present confined jet flow field.

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