Mach number distribution for subsonic flow over a bump.

2DE: 2D Euler CFD tool

Pressure distribution over the test turbine blade, comparison with

Convergence history for subsonic flows over a bump.

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

Recent investigations of shock wave effects and interactions, Advances in Aerodynamics

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

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

Wall roughness effects on the supersonic flow over a circular cylinder

Mach number distribution for subsonic flow over a bump.

Transient CFD of CSP mold (1250 x 100 mm 2 , u c = 6 m/min)

Whitcomb integral airfoil: Mach number contours at M ∞ = 0812 RR = 137