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Analysis Of Supersonic Stall Bending Flutter In Axial Flow Compressor By Actuator Disk Theory by John J Adamczyk
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1NASA Technical Reports Server (NTRS) 19790004832: Analysis Of Supersonic Stall Bending Flutter In Axial-flow Compressor By Actuator Disk Theory
By NASA Technical Reports Server (NTRS)
An analytical model was developed for predicting the onset of supersonic stall bending flutter in axial-flow compressors. The analysis is based on two-dimensional, compressible, unsteady actuator disk theory. It is applied to a rotor blade row by considering a cascade of airfoils. The effects of shock waves and flow separation are included in the model. Calculations show that the model predicts the onset, in an unshrouded rotor, of a bending flutter mode that exhibits many of the characteristics of supersonic stall bending flutter. The validity of the analysis for predicting this flutter mode is demonstrated.
“NASA Technical Reports Server (NTRS) 19790004832: Analysis Of Supersonic Stall Bending Flutter In Axial-flow Compressor By Actuator Disk Theory” Metadata:
- Title: ➤ NASA Technical Reports Server (NTRS) 19790004832: Analysis Of Supersonic Stall Bending Flutter In Axial-flow Compressor By Actuator Disk Theory
- Author: ➤ NASA Technical Reports Server (NTRS)
- Language: English
“NASA Technical Reports Server (NTRS) 19790004832: Analysis Of Supersonic Stall Bending Flutter In Axial-flow Compressor By Actuator Disk Theory” Subjects and Themes:
- Subjects: ➤ NASA Technical Reports Server (NTRS) - ACTUATOR DISKS - SUPERSONIC FLUTTER - TURBOCOMPRESSORS - ANALYSIS (MATHEMATICS) - BENDING - BOUNDARY LAYER SEPARATION - MATHEMATICAL MODELS - ROTOR BLADES (TURBOMACHINERY) - SHOCK WAVES - Adamczyk, J. J.
Edition Identifiers:
- Internet Archive ID: NASA_NTRS_Archive_19790004832
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The book is available for download in "texts" format, the size of the file-s is: 38.68 Mbs, the file-s for this book were downloaded 71 times, the file-s went public at Sat Jul 30 2016.
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