Investigation carried out in test blower; performance of four sets of rotor blades, designed to set up free vortex flow and operating with design pitch-section lift coefficients from 0.31 to 0.99, was studied by making surveys of yaw angles and pressures; tests made in single-stage test blower at Langley Memorial Aeronautical Laboratory of NACA.
Performance of axial-flow fan and compressor blades designed for high loadings
Nat Advisory Committee Aeronautics -- Tech Note
1947
13 pages
18 Supp Plates
Report
English
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Numerical Investigation of Tandem Airfoils for Subsonic Axial-Flow Compressor Blades
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