Numerical simulation of interaction of long-wave disturbances with a shock wave on a wedge for the problem of mode decomposition of supersonic flow oscillations

2016 ◽  
Author(s):  
S. V. Kirilovskiy ◽  
T. V. Poplavskaya ◽  
I. S. Tsyryulnikov
Keyword(s):  
Numerical Simulation ◽  
Shock Wave ◽  
Supersonic Flow ◽  
Wave Disturbances ◽  
Long Wave ◽  
Mode Decomposition ◽  
Flow Oscillations

Microwave discharge initiated by double laser spark in a supersonic airflow

2015 ◽  
Vol 81 (3) ◽  
Author(s):  
R. S. Khoronzhuk ◽  
A. G. Karpenko ◽  
V. A. Lashkov ◽  
D. P. Potapeko ◽  
I. Ch. Mashek
Keyword(s):  
Numerical Simulation ◽  
Shock Wave ◽  
Experimental Study ◽  
Supersonic Flow ◽  
Internal Structure ◽  
Microwave Discharge ◽  
Breakdown Threshold ◽  
Laser Spark ◽  
And Control ◽  
Good Agreement

In this paper, we report the results of an experimental study of microwave (MW) discharge in the supersonic flow initiated by the laser spark and numerical simulation of multiple laser spark shockwave structures in airflow. The MW discharge initiation has been produced by single and double laser sparks. By using different spatial and temporal configuration of laser sparks in supersonic flow, we demonstrate the feasibility of an MW breakdown threshold decrease and control over shape and location of MW plasma. Calculation of laser spark shock wave structures shows good agreement with experimental shadow photographs both in the front shock wave diameter and its internal structure.

NUMERICAL SIMULATION OF THE COMPACTION EFFECT DURING SHOCK WAVE € PARTICLE LAYER NUMERICAL SIMULATION OF THE COMPACTION EFFECT DURING SHOCK WAVE-PARTICLE LAYER INTERACTION

2020 ◽  
Author(s):  
YA. E. POROSHYNA ◽  
◽  
P. S. UTKIN ◽  
Keyword(s):  
Numerical Simulation ◽  
Shock Wave ◽  
Dust Explosion ◽  
Dense Particle ◽  
Layer Interaction ◽  
Particle Layer ◽  
Complex Process ◽  
Impermeable Wall

The problem of shock wave - dense particle layer interaction is a fundamental basis for the study of a more complex process of dust explosion or dust-layered detonation. The work presents results of numerical simulation of the experiment on interaction of an SW with particles layer deposited on the impermeable wall.

Experimental Research of Gasdynamic Liquid Drops Breakup in the Supersonic Flow with an Oblique Shock Wave

2020 ◽  
Author(s):  
K. Yu. Arefyev ◽  
O. V. Guskov ◽  
A. N. Prokhorov ◽  
A. S. Saveliev ◽  
E. E. Son ◽  
...  
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Experimental Research ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Liquid Drops

scholarly journals Analysis of transonic buffet using dynamic mode decomposition

2021 ◽  
Vol 62 (4) ◽  
Author(s):  
Antje Feldhusen-Hoffmann ◽  
Christian Lagemann ◽  
Simon Loosen ◽  
Pascal Meysonnat ◽  
Michael Klaas ◽  
...  
Keyword(s):  
Shock Wave ◽  
Flow Field ◽  
Acoustic Waves ◽  
Feedback Loop ◽  
Measurement Data ◽  
Dynamic Mode Decomposition ◽  
Recirculation Region ◽  
Dynamic Mode ◽  
Mode Decomposition ◽  
Transonic Buffet

AbstractThe buffet flow field around supercritical airfoils is dominated by self-sustained shock wave oscillations on the suction side of the wing. Theories assume that this unsteadiness is driven by a feedback loop of disturbances in the flow field downstream of the shock wave whose upstream propagating part is generated by acoustic waves. High-speed particle-image velocimetry measurements are performed to investigate this feedback loop in transonic buffet flow over a supercritical DRA 2303 airfoil. The freestream Mach number is $$M_{\infty } = 0.73$$ M ∞ = 0.73 , the angle of attack is $$\alpha = 3.5^{\circ }$$ α = 3 . 5 ∘ , and the chord-based Reynolds number is $${\mathrm{Re}}_{c} = 1.9\times 10^6$$ Re c = 1.9 × 10 6 . The obtained velocity fields are processed by sparsity-promoting dynamic mode decomposition to identify the dominant dynamic features contributing strongest to the buffet flow field. Two pronounced dynamic modes are found which confirm the presence of two main features of the proposed feedback loop. One mode is related to the shock wave oscillation frequency and its shape includes the movement of the shock wave and the coupled pulsation of the recirculation region downstream of the shock wave. The other pronounced mode represents the disturbances which form the downstream propagating part of the proposed feedback loop. The frequency of this mode corresponds to the frequency of the acoustic waves which are generated by these downstream traveling disturbances and which form the upstream propagating part of the proposed feedback loop. In this study, the post-processing, i.e., the DMD, is highlighted to substantiate the existence of this vortex mode. It is this vortex mode that via the Lamb vector excites the shock oscillations. The measurement data based DMD results confirm numerical findings, i.e., the dominant buffet and vortex modes are in good agreement with the feedback loop suggested by Lee. Graphic abstract

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