Comparative Study of Stagnation Point Anomalies by Means of Shock Capturing and Shock Fitting Unstructured Codes

The two-dimensional, hypersonic (M = 17.605), laminar flow (Re = 376930) past the forebody of a circular cylinder has been simulated by means of a vertex-centred CFD code using linear triangular elements. Two different approaches have been used to simulate the strong detached bow shock: shock-capturing on anisotropically refined meshes and shock-fitting. Concerning the boundary layer mesh, the distribution of gridpoints has been kept constant, while three different connectivity patterns have been examined. When looking at wall quantities such as pressure, skin friction and heat transfer these appear to be more heavily affected by the boundary layer mesh than by the numerical model used to simulate the detached shock wave.