Receptivity and transition control of swept-wing boundary-layers - Effects of surface curvature and nonlinearity

2001 ◽  
Author(s):  
Erik Janke
Keyword(s):  
Boundary Layers ◽  
Surface Curvature ◽  
Swept Wing ◽  
Transition Control

scholarly journals Evolution of mass flow and total temperature pulsations in flat-plate and swept-wing boundary layers at Mach 2 and 2.5

2020 ◽  
Vol 1677 ◽  
pp. 012033
Author(s):  
A A Yatskikh ◽  
A D Kosinov ◽  
N V Semionov ◽  
Y G Ermolaev ◽  
A V Panina ◽  
...  
Keyword(s):  
Flat Plate ◽  
Boundary Layers ◽  
Mass Flow ◽  
Swept Wing ◽  
Temperature Pulsations ◽  
Total Temperature

Effect of short regions of surface curvature on compressible turbulent boundary layers

AIAA Journal ◽  
1990 ◽  
Vol 28 (1) ◽  
pp. 113-119 ◽  
Author(s):  
David Degani ◽  
Alexander J. Smits
Keyword(s):  
Boundary Layers ◽  
Turbulent Boundary Layers ◽  
Surface Curvature

Surface Curvature Effects on Three-Dimensional Blunt-Body Boundary Layers

AIAA Journal ◽  
1979 ◽  
Vol 17 (2) ◽  
pp. 133-134 ◽  
Author(s):  
D. L. Dwoyer ◽  
Clark H. Lewis ◽  
P. R. Gogineni
Keyword(s):  
Boundary Layers ◽  
Blunt Body ◽  
Three Dimensional ◽  
Surface Curvature ◽  
Curvature Effects ◽  
Body Boundary

Control of a swept-wing boundary layer using ring-type plasma actuators

2018 ◽  
Vol 844 ◽  
pp. 36-60 ◽  
Author(s):  
Nima Shahriari ◽  
Matthias R. Kollert ◽  
Ardeshir Hanifi
Keyword(s):  
Boundary Layer ◽  
Cross Flow ◽  
Plasma Actuators ◽  
Swept Wing ◽  
Ring Type ◽  
Transition Control ◽  
Turbulent Transition ◽  
Roughness Elements ◽  
Order Of Magnitude ◽  
Induced Velocity

Application of ring-type plasma actuators for control of laminar–turbulent transition in a swept-wing boundary layer is investigated thorough direct numerical simulations. These actuators induce a wall-normal jet in the boundary layer and can act as virtual roughness elements. The flow configuration resembles experiments by Kim et al. (2016 Technical Report. BUTERFLI Project TR D3.19, http://eprints.nottingham.ac.uk/id/eprint/46529). The actuators are modelled by the volume forces computed from the experimentally measured induced velocity field at the quiescent air condition. Stationary and travelling cross-flow vortices are triggered in the simulations by means of surface roughness and random unsteady perturbations. Interaction of vortices generated by actuators with these perturbations is investigated in detail. It is found that, for successful transition control, the power of the actuators should be increased to generate jet velocities that are one order of magnitude higher than those used in the experiments by Kim et al. (2016) mentioned above.

Transition Control for a Swept Wing by Crossflow Stabilization Using Plasma Actuators

2020 ◽  
Author(s):  
Takashi Matsuno ◽  
Hirotaka Esaki ◽  
Kaito Tanaka ◽  
Hikaru Aono ◽  
Dongyoun Kwak
Keyword(s):  
Plasma Actuators ◽  
Swept Wing ◽  
Transition Control
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