scholarly journals Shock-vortex shear-layer interaction in the transonic flow around a supercritical airfoil at high Reynolds number in buffet conditions

2015 ◽  
Vol 55 ◽  
pp. 276-302 ◽  
Author(s):  
Damien Szubert ◽  
Fernando Grossi ◽  
Antonio Jimenez Garcia ◽  
Yannick Hoarau ◽  
Julian C.R. Hunt ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Shear Layer ◽  
Transonic Flow ◽  
High Reynolds Number ◽  
Supercritical Airfoil ◽  
Layer Interaction ◽  
High Reynolds

Thin Shear Layer Structures in High Reynolds Number Turbulence

2013 ◽  
Vol 92 (3) ◽  
pp. 607-649 ◽  
Author(s):  
Julian C. R. Hunt ◽  
Takashi Ishihara ◽  
Nicholas A. Worth ◽  
Yukio Kaneda
Keyword(s):  
Reynolds Number ◽  
Shear Layer ◽  
High Reynolds Number ◽  
Layer Structures ◽  
High Reynolds

Development of a New Algorithm for Modeling Viscous Transonic Flow on Unstructured Grids at High Reynolds Numbers

2020 ◽  
Vol 143 (2) ◽  
Author(s):  
Rozie Zangeneh
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Turbulent Flows ◽  
Transonic Flow ◽  
High Reynolds Number ◽  
Unstructured Grids ◽  
Separation Bubble ◽  
Aircraft Design ◽  
Finite Volume Scheme ◽  
High Reynolds

Abstract This study investigates a new algorithm for modeling viscous transonic flow at high Reynolds number cases suitable for unstructured grids. The challenge of modeling viscous transonic flow around airfoils becomes intense at high Reynolds number cases due to a variety of flow regimes encountered, such as boundary layer growth and the shockwave/turbulent boundary-layer interaction, accompanied by large separation bubble. Therefore, it is highly demanded to develop robust and efficient models that can capture the shock-induced problems of turbulent flows for aircraft design purposes. The new model is essentially a hybrid algorithm to address the conflict between turbulence modeling and shock-capturing requirements. A skew-symmetric form of a collocated finite volume scheme with minimum aliasing errors was implemented to model the turbulent region in the combination of a semidiscrete, central difference scheme to capture discontinuities with adequately low numerical dissipation for the minimal effect on turbulent flows. To evaluate the effectiveness of the model, it was tested in three conventional cases. The computational results are close to measured data for predicting the shock locations. This implies that the model is able to predict the scale of the separation bubble and the main characteristics of turbulent transonic flow adequately.

Airfoil Flow Visualization and Pressure Measurements in High-Reynolds-Number Transonic Flow

AIAA Journal ◽  
2003 ◽  
Vol 41 (8) ◽  
pp. 1405-1412 ◽  
Author(s):  
Herbert Olivier ◽  
Thomas Reichel ◽  
Mitja Zechner
Keyword(s):  
Reynolds Number ◽  
Flow Visualization ◽  
Transonic Flow ◽  
High Reynolds Number ◽  
Pressure Measurements ◽  
Airfoil Flow ◽  
High Reynolds
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