NASA NTRS · 19830000629
Analyzing Flow Fields in Axial-Compressor Rotors and Stators
Abstract
Computer program, BLADE3D, developed for analysis of inviscid threedimensional flow fields in single blade passage of axial-compressor rotor or stator. Applicable to arbitrary axial-compressor hub, tip, and blade geometries, including blades with part-span dampers. Also used for axial turbines but with lowered resolution of flows about blunt leading and trailing edges. Analysis method valid for subsonic, transonic and supersonic flows, including choked flows.
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Thompkins, W. J., Jr.. 1984-11-01. Analyzing Flow Fields in Axial-Compressor Rotors and Stators. https://ntrs.nasa.gov/citations/19830000629
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