VMFL071
VMFL071
Mid-Span Flow Over a Goldman Stator Blade
Overview
Reference |
Goldman, L.G., & McLallin, K.L. (1977). Cold-Air Annular Cascade Investigation of Aerodynamic Performance of Core-Engine-Cooled Turbine Vanes: In Solid Vane Performance and Facility Description, NASA Technical Memorandum X-3224. |
Solver | Ansys Fluent |
Physics/Models |
Turbomachinery |
Input File |
VMFL071_FLUENT.cas.h5
|
Project Files | Link to Project Files Download Page |
Test Case
Airflow over a Goldman stator blade at the mid-span is considered. This 2D analysis provides insight into Ansys Fluent's ability to predict the complicated flow features typical of turbomachinery applications. The geometry of the domain under consideration is shown in the figure below. The inlet and the outlet are located approximately 0.03 m away from the blade's leading and trailing edges, respectively. They are located where their presence does not affect predictions near the blade.
Material Properties | Geometry | Boundary Conditions |
---|---|---|
Fluid: Air Density: Ideal gas Viscosity: 1.78e-05 |
Dimensions of the domain: ~ 0.1 m x 0.12 m |
Inlet velocity: 71.75 m/s Translational periodic boundary condition on the top and bottom walls simulate the test section mid-span. |