WANG, Study of the shock motion in a hypersonic shock system/turbulent bound- ary layer interaction, Exp. Fluids, 19 (1995), pp. 143-149.LEE C B,WANG S.Study of the shock motion in a hy- personic shock system/turbulent boundary layer interac- tion[J].Experiments in Fluids,1995,19(...
Wall pressure fluctuations and surface heat transfer signals have been measured in the hypersonic turbulent boundary layer over a number of compression-corner models. The distributions of the separation shock oscillation frequencies and periods have been calculated using a conditional sampling algorithm. In...
Direct Numerical Simulations of Hypersonic Boundary-Layer Transition for a straight cone at Mach 5 Direct Numerical Simulations (DNS) were carried out in order to investigate laminar-turbulent boundary-layer transition for a sharp 7掳 half-angle straight... C Hader,N Deng,HF Fasel - Fluid Dynamic...
Test Problem 1 : Flow Over a Slender Cone Test Problem 2 : Turbulent Base Flow Research on Hypersonic Boundary-Layer Stability with High-Temperature Effects Chapter© 2019 Hypersonic Shock Wave Boundary Layer Interaction Studies on a Flat Plate at Elevated Surface Temperature Chapter Abbreviations cp...
The effects of convex curvature on the outer structure of a Mach 4.9 turbulent boundary layer (Reθ= 4.7 × 104) are investigated using condensate Rayleigh scattering and analyzed using spatial correlations, intermittency, and fractal theory. It is found that the post-expansion boundary layer struc...
In the present study, the response of a hypersonic turbulent boundary layer to a smooth and rough surface along a sharp right-circular cone is examined. Tests were conducted at an inflow of Ma = 6 and Re = 16 Million per meter in the hypersonic wind tunnel H2K at DLR Cologne. The ...
The models used for the charts were equilibrium, thermochemical non-equilibrium, or frozen core flows coupled with either laminar or turbulent (from the nozzle throat) boundary layers. 4.5.7 EXPERIMENTAL TECHNIQUES 4.5.7.1 PITOT PROBE TECHNIQUE In a supersonic wind tunnel one technique currently ...
(as large as 1000 K across 4 mm), which generates stresses of order 100 MPa due to non-uniform thermal expansion. If these stresses are above the materials’ flow stress at the peak temperature, the tip will deform and affect the boundary layer, potentially causing a laminar-to-turbulent ...
On Unsteadiness in 2-D and 3-D Shock Wave Turbulent Boundary Layer Interactions Shock-boundary layer interactions (SBLIs) are ubiquitous occurrences in supersonic and hypersonic vehicles and have the tendency to inhibit their structural and aerodynamic performance. For example, in the inlets and isol...
Large-Eddy Simulation of a Three-Dimensional Hypersonic Shock Wave/Turbulent Boundary Layer Interaction of a Single-Fin The three-dimensional (3D) shock wave/turbulent boundary layer interaction (SWTBLI) of a hypersonic flow passing a single-fin placed on a flat-plate at Mach 5 and Re=3.7 脳...