Mach number distribution for subsonic flow over a bump.

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On the challenge of five-hole-probe measurements at high subsonic Mach numbers in the wake of transonic turbine cascades

Full article: A COMPARATIVE ASSESSMENT WITHIN A MULTIGRID ENVIRONMENT OF SEGREGATED PRESSURE-BASED ALGORITHMS FOR FLUID FLOW AT ALL SPEEDS

Effects of Mach Number on the Performance of a Diverterless Supersonic Inlet

Sketch of scour downstream of an apron.

Pressure contours for flow over subsonic bump: M ∞ = 0.2, Re = 3 × 10 6 .

Wall roughness effects on the supersonic flow over a circular cylinder

Experimental and numerical investigation on a supersonic inlet with large bleed window, The Aeronautical Journal

Convergence history for subsonic flows over a bump.

Pressure distribution at the blades and side wall and the entropy

Jiří FÜRST, Professor, Czech Technical University in Prague, Prague, ČVUT, Faculty of Mechanical Engineering (FS)

Locations denoted by A and B at which near-field spectra

Out-of-plane deflection at blade tip for an inflow velocity of 50 m s .

of radiative and convective heat transfer per unit length of radiant

PDF) On the implicit density based OpenFOAM solver for turbulent compressible flows

Jiří FÜRST, Professor, Czech Technical University in Prague, Prague, ČVUT, Faculty of Mechanical Engineering (FS)