Stability analysis of steady supersonic flow regimes past infinite wedge

1995 ◽  
Vol 36 (2) ◽  
pp. 308-321 ◽  
Author(s):  
A. M. Blokhin ◽  
A. D. Birkin
Keyword(s):  
Stability Analysis ◽  
Supersonic Flow ◽  
Flow Regimes ◽  
Infinite Wedge

Flow Around a Conical Nose with Rounded Tail Projectile for Subsonic, Transonic, and Supersonic Flow Regimes : A Numerical Study

2014 ◽  
Vol 64 (6) ◽  
pp. 509-516
Author(s):  
Amitesh Kumar ◽  
◽  
H.S. Panda ◽  
T.K. Biswal ◽  
R. Appavuraj ◽  
...  
Keyword(s):  
Supersonic Flow ◽  
Numerical Study ◽  
Flow Regimes

An Euler-Based Throughflow Approach for an Axial Turbine at Supersonic Flow Regimes

2021 ◽  
Author(s):  
Sebastian Föllner ◽  
Dieter Brillert ◽  
FriedrichKarl Benra
Keyword(s):  
Supersonic Flow ◽  
Flow Regimes ◽  
Axial Turbine

Stability analysis of a fractional viscoelastic plate strip in supersonic flow under axial loading

Meccanica ◽  
2016 ◽  
Vol 52 (7) ◽  
pp. 1495-1502 ◽  
Author(s):  
Mojtaba Asgari ◽  
Mohammad Reza Permoon ◽  
Hassan Haddadpour
Keyword(s):  
Stability Analysis ◽  
Supersonic Flow ◽  
Axial Loading ◽  
Viscoelastic Plate ◽  
Plate Strip

scholarly journals Hysteresis in Supersonic Flow Past a Plane Cascade of Cylindrical Rods

2021 ◽  
Vol 56 (6) ◽  
pp. 886-896
Author(s):  
S. V. Guvernyuk ◽  
F. A. Maksimov
Keyword(s):  
Mach Number ◽  
Supersonic Flow ◽  
Stokes Equations ◽  
Aerodynamic Drag ◽  
Flow Regimes ◽  
Wake Flow ◽  
Computational Technique ◽  
Infinite Plane ◽  
Continuous Increase ◽  
Number Range

Abstract— The results of numerical simulation of the interaction of supersonic flow with a permeable screen in form of an infinite plane cascade (lattice) of circular cylinders are given. The interaction regime in which the shocks ahead of the cylinders are localized on the scale of the cascade step is considered. The multi-block computational technique in which the viscous boundary layers are resolved by means of local grids using the Navier–Stokes equations, while the effects of inteferrence between the shock-wave structures in supersonic wake are described within the framework of Euler’s equations. The action of shock waves induced by the neighboring elements of lattice to the near-wake region behind the intermediate elements can ambiguously affect the aerodynamic lattice performance as well as generate time-dependent phenomena in the wake. The flow regimes are classified depending on continuous increase and decrease in the free-stream supersonic air flow in the Mach number range from 2.4 to 4.2 with reference to the lattice of the 80% permeability. The sources of the hysteresis behavior of the lattice aerodynamic drag with respect to the Mach number and the mechanisms of the onset of self-oscillating wake flow regimes are discussed.

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