Pressure Pulsations on a Flat Plate Normal to an Underexpanded Supersonic Jet

AIAA Journal ◽  
1978 ◽  
Vol 16 (6) ◽  
pp. 634-636 ◽  
Author(s):  
Lloyd H. Back ◽  
Virendra Sarohia
Keyword(s):  
Flat Plate ◽  
Supersonic Jet ◽  
Pressure Pulsations ◽  
Underexpanded Supersonic Jet

Experimental Study of Underexpanded Supersonic Jet Impingement on an Inclined Flat Plate

AIAA Journal ◽  
2006 ◽  
Vol 44 (11) ◽  
pp. 2691-2699 ◽  
Author(s):  
Yusuke Nakai ◽  
Nobuyuki Fujimatsu ◽  
Kozo Fujii
Keyword(s):  
Experimental Study ◽  
Flat Plate ◽  
Supersonic Jet ◽  
Jet Impingement ◽  
Underexpanded Supersonic Jet

On the impingement of a supersonic jet on a flat plate

1969 ◽  
Vol 20 (1) ◽  
pp. 15-18 ◽  
Author(s):  
Chong-Wei Chu ◽  
S. A. Powers ◽  
H. Ziegler
Keyword(s):  
Flat Plate ◽  
Supersonic Jet

scholarly journals Feedback loop and upwind-propagating waves in ideally expanded supersonic impinging round jets

2017 ◽  
Vol 823 ◽  
pp. 562-591 ◽  
Author(s):  
Christophe Bogey ◽  
Romain Gojon
Keyword(s):  
Flat Plate ◽  
Acoustic Waves ◽  
Feedback Loop ◽  
Supersonic Jet ◽  
Vortex Sheet ◽  
Impinging Jets ◽  
Loop Model ◽  
Turbulent Structures ◽  
Fourier Decomposition ◽  
Pressure Fields

The aeroacoustic feedback loop establishing in a supersonic round jet impinging on a flat plate normally has been investigated by combining compressible large-eddy simulations and modelling of that loop. At the exit of a straight pipe nozzle of radius $r_{0}$, the jet is ideally expanded, and has a Mach number of 1.5 and a Reynolds number of $6\times 10^{4}$. Four distances between the nozzle exit and the flat plate, equal to $6r_{0}$, $8r_{0}$, $10r_{0}$ and $12r_{0}$, have been considered. In this way, the variations of the convection velocity of the shear-layer turbulent structures according to the nozzle-to-plate distance are shown. In the spectra obtained inside and outside of the flow near the nozzle, several tones emerge at Strouhal numbers in agreement with measurements in the literature. At these frequencies, by applying Fourier decomposition to the pressure fields, hydrodynamic-acoustic standing waves containing a whole number of cells between the nozzle and the plate and axisymmetric or helical jet oscillations are found. The tone frequencies and the mode numbers inferred from the standing-wave patterns are in line with the classical feedback-loop model, in which the loop is closed by acoustic waves outside the jet. The axisymmetric or helical nature of the jet oscillations at the tone frequencies is also consistent with a wave analysis using a jet vortex-sheet model, providing the allowable frequency ranges for the upstream-propagating acoustic wave modes of the jet. In particular, the tones are located on the part of the dispersion relations of the modes where these waves have phase and group velocities close to the ambient speed of sound. Based on the observation of the pressure fields and on frequency–wavenumber spectra on the jet axis and in the shear layers, such waves are identified inside the present jets, for the first time to the best of our knowledge, for a supersonic jet flow. This study thus suggests that the feedback loop in ideally expanded impinging jets is completed by these waves.

Numerical study of the ejection properties of a jet flowing into flooded space

2020 ◽  
Author(s):  
A.Yu. Lutsenko ◽  
V.A. Kriushin
Keyword(s):  
Pressure Distribution ◽  
Nozzle Exit ◽  
Software Package ◽  
Numerical Study ◽  
Supersonic Jet ◽  
Underlying Surface ◽  
Ansys Fluent ◽  
Fluent Software ◽  
Underexpanded Supersonic Jet ◽  
Jet Axis

The purpose of the study was to carry out a numerical simulation of the interaction of an underexpanded supersonic jet flowing into a flooded space with a normally located obstacle, and with the underlying surface. We performed the calculations in the ANSYS Fluent software package and presented flow patterns. For the case when the obstacle is located normally to the axis of the jet, we compared the pressure distribution in the radial direction with experimental data and made a conclusion about the changes in the integral load on the wall with a change in the distance to the nozzle exit. For the case when the obstacle is parallel to the jet axis, we presented the pressure distribution along the wall in the plane of symmetry, estimated the relative net force acting on the underlying surface, analyzed the nature of its change at various values of the off-design coefficient, the Mach number on the nozzle exit and the distance to the jet axis.

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