The flow field between two blades was analyzed numerically by solving the
steady, two dimensional and incompressible (time-mass averaged Navier- Stokes
equations). The (κ-ε) turbulent model was used to simulate the condition of the
momentum equation and to obtain the eddy viscosity. The SIMPLE algorithm is
used to satisfy velocity-pressure coupling method and to satisfy the conservation
of mass. A computer code was constructed in this work using FORTRAN 90
language to simulate the flow. The numerical results were compared with
experimental results of other researcher for flow through the cascade of axial
compressor, and were found to be in a good agreement. Three different airfoils
common, used for axial flow compressors blades, were investigated in the present
study. The study shows that stall happens. At incidence angles (-80 to 70) for
NACA 65(12)10 and (-90 to 30) for NACA 65(18)10 and (-70 to 90) for NACA
65(8)10. The result also show that stall happens when the total pressure loss is
greater than 0.06 for NACA 65(8)10 when stagger angle is greater than 450 stall
happens for total pressure loss less 0.06 as the outlet flow angle decreases.
However, the quasi-three dimensional, steady, incompressible, turbulent, adiabatic
and single-phase fluid flow inside the blade-to-blade passage of an axial flow
compressor stator was also studied and the study shows that Stall was seen to take
place at blade tips during starting.