Technical Note

Technical Note
Author:
Publisher:
Total Pages: 414
Release: 1958
Genre: Aeronautics
ISBN:

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Axial-flow Compressors

Axial-flow Compressors
Author: Ronald H. Aungier
Publisher: American Society of Mechanical Engineers
Total Pages: 386
Release: 2003
Genre: Science
ISBN:

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This book provides a thorough description of an aerodynamic design and analysis systems for Axial-Flow Compressors. It describes the basic fluid dynamic and thermodynamic principles, empirical models and numerical methods used for the full range of procedures and analytical tools that an engineer needs for virtually any tupe of Axial-Flow Compressor, aerodynamic design or analysis activity. It reviews and evaluates several design strategies that have been recommended in the literature or which have been found to be effective. It gives a complete description of an actual working system, such that readers can implement all or part of the system. Engineers responsible for developing, maintaining of improving design and analysis systems can benefit greatly from this type of reference. The technology has become so complex and the role of computers so pervasive that about the only way this can be done today is to concentrate on a specific design and analysis system. The author provides practical methodology as well as the details needed to implement the suggested procedures.

Index of NACA Technical Publications

Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Total Pages: 274
Release: 1953
Genre: Aeronautics
ISBN:

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Flutter Analysis of Rectangular Wings of Very Low Aspect Ratio

Flutter Analysis of Rectangular Wings of Very Low Aspect Ratio
Author: Robert William Fralich
Publisher:
Total Pages: 652
Release: 1958
Genre: Aerofoils
ISBN:

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A flutter analysis, employing slender-body aerodynamic theory and thin-plate theory, is made for rectangular wings of very low aspect ratio with a constant thickness. The spanwise variation of wing deflection is assumed to be given by a parabola, and the chordwise variation is allowed complete freedom. The results show the vsriation of flutter speed and male shape with aspect ratio. Comparisons are made with additional resuits obtained by approximating the chordwise deflection shape by use of parabolic or cubic curves. The analysis shows that the cubic approximation gives good resuits for a ratio of chord to semispan less than 3.