16 research outputs found
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NACA Technical Notes
From Introduction: "A solution of the type of reference 2 is necessary to give the stream-sheet thickness and curvature for the blade-to-blade (S1 surface) solution considered in this report. The equations for the solution of the S1 surface of revolution are presented in reference 3. The purpose of the subject report is to continue the work of reference 3 by applying the method to a specific problem in order that the practicability of the method and the time involved in computing a solution may be determined.
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NACA Research Memorandums
Report presenting an investigation conducted on an NACA axial-flow single-stage compressor with a 14-inch diameter and a 0.9 hub-tip ratio to determine the magnitude of the blade force variation due to the flow fluctuations caused by rotating stall. Results regarding steady-state blade forces, shapes of steady-state force curves, time variation in weight flow, oscillograms of strain-gage output, and effect of damping are provided
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NACA Technical Notes
Report presenting an analysis of the supersonic flow in two two-dimensional high-solidity cascades and in a partly supersonic symmetrical nozzle. A method is developed for the determination of the supersonic flow along stream surfaces of revolution in turbomachines. In addition to their use in direct problems, the equations can be used to design blade elements in supersonic flow along an arbitrary stream filament of revolution in turbomachines