Abstract
A space-marching method was used to predict the viscous flowfield in turbomachinery cascades. Departure solutions were suppressed by modifying the streamwise pressure gradient term in the momentum equations. For staggered cascades a nonperiodic grid system was employed, and appropriate approximations were used in place of the periodicity boundary conditions upstream and downstream of the cascade. The laminar flow through a flat-plate cascade at 45-deg stagger and through a symmetric cascade at zero incidence and stagger was tested first. The method was then used to predict the turbulent flow through compressor cascades composed of NACA 65-series blades. The predicted drag coefficient, turning angle, boundary-layer momentum thicknesses, and velocity profiles were compared with the experimental data; the agreement was good in most cases. The solution of the cases presented was obtained in less than 1 min of CPU time on an IBM 3081 computer.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
