Three-dimensional theory for the steady loading on an annular blade row
Author:
Affiliation:
1. Calspan Corporation, Buffalo, N. Y.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.7788
Reference20 articles.
1. McCune, J. E. "The Three-Dimensional Flow Field of an Axial Compressor Blade Row-Subsonic, Transonic, and Supersonic," Ph.D. Thesis,Cornell Univ., Ithaca, N.Y., 1958.
2. A Three Dimensional Theory of Axial Compressor Blade Rows - Application in Subsonic and Supersonic Flows
3. The Transonic Flow Field of an Axial Compressor Blade Row
4. 4Okurounmu, O. and McCune, J. E. "Three-Dimensional Vortex Theory of Axial Compressor Blade Rows at Subsonic and Transonic Speeds,'M/>L4 Journal, Vol.8, July 1970, pp.1275-1283.
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1. An Unsteady Lifting Surface Theory for Ducted Fan Blades;Journal of Turbomachinery;1993-01-01
2. A note on the Kutta condition in Glauert's solution of the thin aerofoil problem;Journal of Engineering Mathematics;1992-02
3. A note on the Kutta condition in Glauert’s solution of the thin aerofoil problem;Problems in Applied, Industrial and Engineering Mathematics;1992
4. Theory of Blade Design for Large Deflections: Part II—Annular Cascades;Journal of Engineering for Gas Turbines and Power;1984-04-01
5. Theory of Blade Design for Large Deflections: Part I—Two-Dimensional Cascade;Journal of Engineering for Gas Turbines and Power;1984-04-01
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