High-Speed Schlieren Imaging of Disturbances in a Transitional Hypersonic Boundary Layer

2013 ◽  
Author(s):  
Katya Casper ◽  
Steven Beresh ◽  
John Henfling ◽  
Russell Spillers ◽  
Brian Pruett
Keyword(s):  
Boundary Layer ◽  
High Speed ◽  
Hypersonic Boundary Layer ◽  
Schlieren Imaging

High-Speed Schlieren Imaging and Hot-wire Characterization of Cylinder-Induced Hypersonic Shock Boundary Layer Interactions

2018 ◽  
Author(s):  
Andrew Leidy ◽  
Ian T. Neel ◽  
Nathan R. Tichenor ◽  
Rodney D. Bowersox ◽  
John D. Schmisseur
Keyword(s):  
Boundary Layer ◽  
High Speed ◽  
Hot Wire ◽  
Schlieren Imaging ◽  
Hypersonic Shock

High-Speed Schlieren Imaging of Cylinder-Induced Hypersonic-Shock-Wave–Boundary-Layer Interactions

AIAA Journal ◽  
2020 ◽  
Vol 58 (7) ◽  
pp. 3090-3099 ◽  
Author(s):  
Andrew N. Leidy ◽  
Ian T. Neel ◽  
Nathan R. Tichenor ◽  
Rodney D. W. Bowersox
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
High Speed ◽  
Schlieren Imaging ◽  
Wave Boundary Layer ◽  
Hypersonic Shock ◽  
Wave Boundary

scholarly journals Wall pressure beneath a transitional hypersonic boundary layer over an inclined straight circular cone

2020 ◽  
Vol 2 (1) ◽  
Author(s):  
Siwei Dong ◽  
Jianqiang Chen ◽  
Xianxu Yuan ◽  
Xi Chen ◽  
Guoliang Xu
Keyword(s):  
Boundary Layer ◽  
High Frequency ◽  
High Speed ◽  
Low Frequency ◽  
Axial Direction ◽  
Wall Pressure ◽  
Hypersonic Boundary Layer ◽  
High Frequency Signal ◽  
Local Boundary ◽  
Half Angle

AbstractProperties of wall pressure beneath a transitional hypersonic boundary layer over a 7∘ half-angle blunt cone at angle of attack 6∘ are studied by Direct Numerical Simulation. The wall pressure has two distinct frequency peaks. The low-frequency peak with f≈10−50 kHz is very likely the unsteady crossflow mode based on its convection direction, i.e. along the axial direction and towards the windward symmetry ray. High-frequency peaks are roughly proportional to the local boundary layer thickness. Along the trajectories of stationary crossflow vortices, the location of intense high-frequency wall pressure moves from the bottom of trough where the boundary layer is thin to the bottom of shoulder where the boundary layer is thick. By comparing the pressure field with that inside a high-speed transitional swept-wing boundary layer dominated by the z-type secondary crossflow mode, we found that the high-frequency signal originates from the Mack mode and evolves into the secondary crossflow instability.

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