Some supersonic flow regimes on the windward side of V-shaped wings

1992 ◽  
Vol 27 (2) ◽  
pp. 257-266 ◽  
Author(s):  
M. A. Zubin ◽  
N. A. Ostapenko
Keyword(s):  
Supersonic Flow ◽  
Flow Regimes ◽  
Windward Side

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

Experimental study of supersonic flow past wedges with longitudinal grooves on the windward side

1993 ◽  
Vol 28 (2) ◽  
pp. 296-298 ◽  
Author(s):  
V. I. Voronin ◽  
G. S. Ulyanov ◽  
A. I. Shvetz
Keyword(s):  
Experimental Study ◽  
Supersonic Flow ◽  
Windward Side ◽  
Flow Past

scholarly journals Numerical Analysis on the Crosswind Influence Around a Generic Train Moving on Different Bridge Configurations

2021 ◽  
Vol 89 (2) ◽  
pp. 76-98
Author(s):  
Izuan Amin Ishak ◽  
Nurshafinaz Maruai ◽  
Fadhilah Mohd Sakri ◽  
Rahmah Mahmudin ◽  
Nor Afzanizam Samiran ◽  
...  
Keyword(s):  
Bluff Body ◽  
Flow Regimes ◽  
Flow Behaviour ◽  
Windward Side ◽  
Leeward Side ◽  
Rolling Moment ◽  
Flow Angle ◽  
Freestream Velocity ◽  
Aerodynamic Properties ◽  
Bridge Girder

In this article, a numerical approach is applied to study the flow regimes surround a generic train model travelling on different bridge configurations under the influence of crosswind. The bridge is varies based on the different geometry of the bridge girder. The crosswind flow angle (Ψ) is varied from 0° to 90°. The incompressible flow around the train was resolved by utilizing the Reynolds-averaged Navier-Stokes (RANS) equations combined with the SST k-ω turbulence model. The Reynolds number used, based on the height of the train and the freestream velocity, is 3.7 × 105. In the results, it was found that variations of the crosswind flow angles produced different flow regimes. Two unique flow regimes appear, representing (i) slender body flow behaviour at a smaller range of Ψ (i.e. Ψ ≤ 45°) and (ii) bluff body flow behaviour at a higher range of Ψ (i.e. Ψ ≥ 60°). As the geometries of the bridge girder were varied, the bridge with the wedge girder showed the worst aerodynamic properties with both important aerodynamic loads (i.e. side force and rolling moment), followed by the triangular girder and the rectangular girder. This was due to the flow separation on the windward side and flow structure formation on the leeward side, both of which are majorly influenced by the flow that moved from the top and below of the bridge structures.

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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