Numerical prediction of unsteady transitional boundary layer flow due to rotor-stator interaction
Author:
Affiliation:
1. Pennsylvania State Univ., University Park
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1997-2752
Reference24 articles.
1. Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part 1—Quasi-Steady Flow Field and Comparison With Steady-State Data
2. Solomon, W. J. and Walker, G. J. "Observations of Wake-Induced Transition on an Axial Compressor Blade,"ASMEPaper 95-GT-381,1995.
3. Halstead,D.E. etal."BoundaryLayerDevelopment in Axial Compressors and Turbines," Part 1: CompositePicture, Part 2: Compressors, Part 3:LP Turbines,Part 4: ComputationsandAnalysis,ASME 95-GT-461,462,464,1995.
4. The 1991 IGTI Scholar Lecture: The Role of Laminar-Turbulent Transition in Gas Turbine Engines
5. Computation and Simulation of Wake-Generated Unsteady Pressure and Boundary Layers in Cascades: Part 1—Description of the Approach and Validation
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