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Implementation of weighted essentially non‐oscillatory scheme for unsteady and steady compressible flow in pressure‐based algorithm - Balaj - 2021 - International Journal for Numerical Methods in Fluids - Wiley Online Library
Surface heat transfer coefficient for VKI MUR 241 Cascade.
Locations denoted by A and B at which near-field spectra
An Investigation on the Effect of Changing Bump Geometry on a 2D Supersonic Inlet
Experimental investigation of jet-induced wall pressure fluctuations over a tangential flat plate at two Reynolds numbers
Effects of Mach Number on the Performance of a Diverterless Supersonic Inlet
Pressure distribution over the test turbine blade, comparison with
Cross-sectional (x − y) views of the computational domain and the grid
PDF) On the implicit density based OpenFOAM solver for turbulent compressible flows
Subsonic Flow - an overview
A supersonic flow at Mach 3.0 is to be solved down via normal shock in a diverging channel. For the conditions shown in the figure below, find p2/p1 and pe/pi.
Jiří FÜRST, Professor, Czech Technical University in Prague, Prague, ČVUT, Faculty of Mechanical Engineering (FS)
PDF) On the implicit density based OpenFOAM solver for turbulent compressible flows
Implementation of weighted essentially non‐oscillatory scheme for
