[PDF] Top 20 Shock Wave Turbulent Boundary Layer Interaction in a 2-D Compression Corner

... of shock-wave / turbulent boundary layer interactions (SWTBLIs) is frequently encountered on the surfaces of aeronautical/aerospace devices like air intake compression ramps of ... See full document

... The experimental investigation was undertaken at the Turbulent Shear Flow Laboratory at the North Carolina State University. This facility is a blow down type variable Mach number wind tunnel with a Mach number ... See full document

... The hypersonic air breathing propulsion system consists of Scramjet (supersonic combustion ramjet) and ramjet plays a major role in high-speed engines. In the scramjet, the shock wave plays a vital role in ... See full document

... the interaction between the ejected jet flow and the main crossflow can be ...supersonic boundary layer, the jet was suppressed in the near-wall region of the boundary ...local boundary ... See full document

... the interaction with the normal shock and it further penetrates underneath the main vortex into the near-wall separation region and gets accelerated to supersonic ...normal shock (as shown in ... See full document

... and speed profiles, the code has been validated using two verification approaches. Firstly, the code results have been compared to the Sod’s tube problem (exact solution). Secondly, the code solution is compared with ... See full document

... The snapshot at N=1968 is chosen to reveal the high-frequency undulation observed in the previous section. The contours of radial velocity and axial vorticity within the bottom plane (Plane 9) are shown in figure 6. This ... See full document

... test chamber. The wind tunnel can generate flow at different Mach numbers by changing the contoured nozzles. The nozzle is of circular cross-section and has an outlet diameter of 300 mm. A cluster of eighteen layers of ... See full document

... Shock boundary layer interaction flow features are encountered in many high speed engineering devices such as turbine blades, air wings, intake systems for ram jet engines, ...the shock ... See full document

... 3D turbulent flow through turbine cascades with eddy-viscosity turbulence model complemented with the γ-ζ model of transition to ...of boundary layer edge and is adaptive as long as the whole ... See full document

... bow shock wave and the body is called the shock ...the shock wave and the body becomes smaller ...the shock wave angle will be even smaller ...that shock waves lie ... See full document

... the compression ramp leading edge, with subsequent transducers spaced every ...incoming boundary layer, with at least one transducer under the intermittent region and at least one transducer below ... See full document

... Shock-wave/turbulent boundary layer interactions (SWTBLI) are prevalent phenomena in high- speed flights, which could cause large flow separation and high wall heat flux and strong ... See full document

... [mm], 2 [mm] and 5 [mm], the density increases as time passed after passing the wavefront, but the increasing density decreases ...the boundary layer profile has changed from laminar flow to ... See full document

... layer interaction. It also describes the inviscid flow over a compression corner. Chapter 3 describes the simulation methodology. It presents the introduction to the turbulent models ... See full document

... low-frequency shock motion in ...low-frequency shock unsteadiness), fast FIBs have a low total luminophore count that leads to low luminescent intensity and a poor signal-to-noise ratio (SNR) ... See full document

... on compression ramps are chosen for investigation as it is commonly seen in applications, such as supersonic inlet and some external surfaces in hypersonic ...individual compression ramps, the present study ... See full document

... zone 2 is also very strong, and these fluctuations are weakened with the diffusion of the free-shear ...shear layer by Kelvin–Helmholtz instability can be ...thin layer attached to the wall, but the ... See full document

... oblique shock wave generated by the fin interacts with the turbulent boundary layer on the plate and 24.. results in flow separation.[r] ... See full document

... Shock-wave/turbulent boundary layer interaction (SWTBLI) happens ubiquitously in high-speed vehicles, including tran- sonic airfoils, supersonic inlets, control surfaces of ... See full document