[PDF] Top 20 The effect of Mach number on unstable disturbances in shock/boundary layer interactions

... characteristic-based boundary con- dition is used in order to minimize any reflected ...impinging shock wave, while downstream of the im- pinging shock location the upper boundary condition ... See full document

... section Mach number of 2.5 and unit Reynolds number of ...ramp interactions were used as surrogates for the impinging/reflected SBLIs present in isolator shock ...the effect of ... See full document

... the effect of 3-D relief on a sharp fin SBLI, a myriad of experimental techniques are employed to analyze both the surface and off-body mean flows of a fin placed on a cylindrical ...of shock strengths, ... See full document

... Mach number contours just downstream of the micro VG trailing edge at X = 111 mm (Figure 6.6) clearly show the initial growth of the primary vortex cores. The spanwise extent of the low momentum region is ... See full document

... a Mach 2.3 shock-wave generated by an 8° sharp wedge impinging onto a spatially-developing turbulent boundary layer along a flat plate is carried ... See full document

... the Mach number contour plot for the inviscid supersonic flow over thecompression ...oblique shock exists on the ramp and an abruptchange in flow velocity occurs across the ...thin layer at ... See full document

... The flow field over a compression ramp is formed by the intersection of a flat plate with a wedge of angle 10 0 to the horizontal. The flat plate is given a length of 50 mm and the ramp of another 50mm with 10 0 ... See full document

... turbulent boundary-layer flow over a compression cor- ner at Mach number 3 and Reynolds number Re h ¼ 1685 (based on the inflow momentum ...oblique shock-wave interacting with a ... See full document

... This paper describes numerical simulation of transient flow conditions in shock tube. A two dimensional time accurate Navier-Stokes CFD solver for shock tube applications is developed to perform the ... See full document

... conical-cross Mach number 𝑀 𝑛 are presented in ...normal shock and it further penetrates underneath the main vortex into the near-wall separation region and gets accelerated to supersonic ...normal ... See full document

... in shock – boundary-layer interactions [41,49 – ...of shock-train motion interestingly affects its structure ...turbulent boundary layer, giving insight into their ... See full document

... of shock wave structures in ramjet/scramjet inlet/isolator models in supersonic flow have been ...at Mach 2 both computationally and ...investigate shock wave structures in and around the three ... See full document

... laminar boundary layer into turbulence often occurs via the formation of localized turbulent patches, referred to as turbulent ...any interactions between spots (Krishnan & Sandham ... See full document

... compliant material; it encompasses such a broad range of possible materials with an equally broad way to model and apply them. Understanding how these materials perform in and interact with varying regimes of flow can ... See full document

... This effect is likely due to the increased thickness of the incoming boundary layer at the centerline, which would displace the sonic line upwards by some amount, decreasing the penetration depth of ... See full document

... model shock wave in air and to validate the shock wave properties like Mach number, primary shock strength, reflected shock strength, primary shock wave temperature ratio ... See full document

... absorbing boundary condition in FDTD is required to truncate the computation domain without reflection in the simulation of DNG medium properties and ...absorbing boundary condition for DNG medium has been ... See full document

... the shock wave. In high Mach number shock tube and shock tunnel or any other flow field with strong discontinuities, the tempera- ture variation in the field is large, and the specific ... See full document

... The non-dimensional velocity (u/U) distribution in the downstream flowfield of the SJG was investigated. At X=50mm, the mean freestream velocity (U) was constant at 8.36 m/s, while varies from 0° to 90°. The ... See full document

... A classical point of view is that as the boundary layer becomes instable, it splits from the boundary, enters into the domain and probably disturbs it completly. Kato’s result leads to a change of ... See full document