Figure 6 - uploaded by Reynald Bur
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View of the computational domain. The blue line represents the subsonic injection, the green line the supersonic outflow, the black line the wallslip condition and the red line the adiabatic wall. The mesh features a uniform refinement of Δx=0 .33 in the area of the flat plate. The extended part of the flat plate, downstream of the experimental configuration, has an increasing discretization length, up to Δx=1. In total this amounts to 911 discretization points. Δy=0 .001
Source publication
A transitional shock wave / boundary layer interaction at M=1.6 is investigated using experimental and numerical approaches. A flat plate apparatus installed in a supersonic wind tunnel serves as the basis of the study. Schlieren visualizations and measurements of the heat transfers at the surface of the flat plate provide a characterization of the...
Contexts in source publication
Context 1
... the flat plate is taken into account by an adiabatic wall condition. A schematic of the computational domain is provided in figure 6. at the wall, with a geometric increment over 250 points, which leads to Δy=0 .71 at the top of the domain. ...
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Although airfoil stall has been widely investigated, its origin is still not clearly understood. In this paper we investigate static stall by finding many steady flow solutions around the stall angle and then investigating their stability. In particular, we look for steady unstable modes and deduce a bifurcation scenario from them. In this way we hope to model and then control the stall dynamics. The study is performed on a 2D helicopter blade airfoil OA209 at low Mach number, Ma 0.2, and high Reynolds number, Re=1.8 10^6. A first solution is obtained numerically for an angle of incidence smaller (resp. higher) than the stall angle. This computation is based on a steady RANS computation with the Spalart-Allmaras model. Then Newton’s method (with the Jacobian computed by finite difference) is used to propagate the solution along the upper (resp. lower) branch. Finally, another continuation method, called the pseudo-arclength method, is used to follow the unstable mode
between the two branches.
