scholarly journals Experimental study of a supersonic jet-mixing layer interaction

2004 ◽  
Vol 16 (3) ◽  
pp. 765-778 ◽  
Author(s):  
E. Collin ◽  
S. Barre ◽  
J. P. Bonnet
Keyword(s):  
Experimental Study ◽  
Mixing Layer ◽  
Supersonic Jet ◽  
Jet Mixing ◽  
Layer Interaction

Flow Stucture of Supersonic Underexpanded Jet With Microjets Injection

2013 ◽  
Vol 8 (1) ◽  
pp. 44-55
Author(s):  
Dmitriy Gubanov ◽  
Valeriy Zapryagaev ◽  
Nikolay Kiselev
Keyword(s):  
Flow Structure ◽  
Numerical Study ◽  
Mixing Layer ◽  
Supersonic Jet ◽  
Wave Structure ◽  
Streamwise Vortices ◽  
Jet Mixing ◽  
Underexpanded Jet ◽  
Supersonic Underexpanded Jet ◽  
The Impact

Experimental and numerical study of transversal microjets injection influence on the supersonic underexpanded jet flow structure has been performed. Data of measurements and calculation have acceptable agreement. Interaction of microjets with main supersonic jet sets to a decrease of an initial gasdynamic region. Microjets lead to a longitudinal streamwise vortices generation and a mushroom-like flow structures create on an external jet mixing layer. Dissipation of longitudinal streamwise vortices was observed at the second jet cell. Complex gasdynamic flow structure of the supersonic underexpanded jet interacting with supersonic microjets has been studied for the first time. This structure contains system of complex chock waves and expansion waves spreading from the position of the impact microjets/main jet localization place. Future of interaction process a chock-wave structure of main jet with additional shock waves has been studied

scholarly journals ANALYSIS OF A JET – MIXING LAYER INTERACTION

2002 ◽  
pp. 515-524
Author(s):  
S. Lardeau ◽  
E. Collin ◽  
E. Lamballais ◽  
J. Delville ◽  
S. Barre ◽  
...  
Keyword(s):  
Mixing Layer ◽  
Jet Mixing ◽  
Layer Interaction

Mach waves produced in the supersonic jet mixing layer by shock/vortex interaction

Shock Waves ◽  
2016 ◽  
Vol 26 (3) ◽  
pp. 231-240 ◽  
Author(s):  
H. Oertel Sen ◽  
F. Seiler ◽  
J. Srulijes ◽  
R. Hruschka
Keyword(s):  
Mixing Layer ◽  
Supersonic Jet ◽  
Vortex Interaction ◽  
Jet Mixing ◽  
Mach Waves

scholarly journals Analysis of a jet–mixing layer interaction

2003 ◽  
Vol 24 (4) ◽  
pp. 520-528 ◽  
Author(s):  
S. Lardeau ◽  
E. Collin ◽  
E. Lamballais ◽  
J.P. Bonnet
Keyword(s):  
Mixing Layer ◽  
Jet Mixing ◽  
Layer Interaction

Investigation on the Source Locations of Axisymmetric Screech Tones Utilizing Data from Numerical Simulation

2019 ◽  
Vol 27 (04) ◽  
pp. 1850058
Author(s):  
Incheol Lee ◽  
Duck Joo Lee
Keyword(s):  
Mach Number ◽  
Fourth Order ◽  
Mixing Layer ◽  
Supersonic Jet ◽  
Shock Cell ◽  
Jet Mixing ◽  
Screech Tone ◽  
Runge Kutta Method ◽  
Cell Structures ◽  
Screech Tones

The source locations of axisymmetric modes of screech tones are numerically investigated. Fourth-order optimized compact scheme and fourth-order Runge–Kutta method are used to solve the 2-D axisymmetric Euler equations. The screech tone is successfully reproduced, and the change in wavelength with respect to jet Mach number shows good agreement with the experimental data. At various low supersonic jet Mach numbers, the time-averaged contours of Mach number and root-mean-square pressure are investigated to identify the location of maximum interaction between shock cell structures and vortices. The source locations of two axisymmetric modes, A1 and A2 modes, are distinctly visualized and identified; the screech tones of A1 mode are generated at the apex of fifth shock cell, and the screech tones of A2 mode are generated at the apex of fourth shock cell. Based on the observation, a simple formula for the prediction of axisymmetric modes of screech tones is proposed. The formula is derived based on a form of Rossiter equation, with the assumption of different convection speeds along the jet mixing layer. The proposed formula successfully estimates the frequency of two axisymmetric modes of screech tones, which verifies that the identified source locations of the axisymmetric screech tones are reasonable.

scholarly journals Aspect Ratio Driven Relationship between Nozzle Internal Flow and Supersonic Jet Mixing

Aerospace ◽  
2021 ◽  
Vol 8 (3) ◽  
pp. 78
Author(s):  
Kalyani Bhide ◽  
Kiran Siddappaji ◽  
Shaaban Abdallah
Keyword(s):  
Boundary Layer ◽  
Aspect Ratio ◽  
Nozzle Exit ◽  
Supersonic Jet ◽  
Internal Flow ◽  
Shear Stresses ◽  
Loss Mechanism ◽  
Potential Core ◽  
Jet Mixing ◽  
Aspect Ratios

This work attempts to connect internal flow to the exit flow and supersonic jet mixing in rectangular nozzles with low to high aspect ratios (AR). A series of low and high aspect ratio rectangular nozzles (design Mach number = 1.5) with sharp throats are numerically investigated using steady state Reynolds-averaged Navier−Stokes (RANS) computational fluid dynamics (CFD) with k-omega shear stress transport (SST) turbulence model. The numerical shadowgraph reveals stronger shocks at low ARs which become weaker with increasing AR due to less flow turning at the throat. Stronger shocks cause more aggressive gradients in the boundary layer resulting in higher wall shear stresses at the throat for low ARs. The boundary layer becomes thick at low ARs creating more aerodynamic blockage. The boundary layer exiting the nozzle transforms into a shear layer and grows thicker in the high AR nozzle with a smaller potential core length. The variation in the boundary layer growth on the minor and major axis is explained and its growth downstream the throat has a significant role in nozzle exit flow characteristics. The loss mechanism throughout the flow is shown as the entropy generated due to viscous dissipation and accounts for supersonic jet mixing. Axis switching phenomenon is also addressed by analyzing the streamwise vorticity fields at various locations downstream from the nozzle exit.

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