Shock wave/boundary layer interaction (SWBLI) is a highly critical problem that occurs in aircraft transonic or supersonic flow. This study performed CFD analysis of the ramp flow freestream Mach number 2.79. To secure reliability analysis, adaptive mesh refinement using gradient p sensor was used. Through this, grid sufficient resolution obtained for region shock wave, expansion and separation...

We report on the discovery of mostly horizontal field channels just outside sunspot penumbrae (in the so-called ‘moat’ region) that are seen to sustain supersonic flows (line-of-sight component of 6 km s). The spectral signature of these supersonic flows corresponds to circular polarization profiles with an additional, satellite, third lobe of the same sign as the parent sunspot’ Stokes V blue ...