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Design And Tests Of A Six Stage Axial Flow Compressor Having A Tip Speed Of 550 Feet Per Second And A Flat Operating Characteristic At Constant Speed

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Design And Tests Of A Six Stage Axial Flow Compressor Having A Tip Speed Of 550 Feet Per Second And A Flat Operating Characteristic At Constant Speed

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Author : Willard R. Westphal
language : en
Publisher:
Release Date : 1958

Design And Tests Of A Six Stage Axial Flow Compressor Having A Tip Speed Of 550 Feet Per Second And A Flat Operating Characteristic At Constant Speed written by Willard R. Westphal and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with Axial flow compressors categories.

A six-stage axial-flow compressor with a tip speed of 550 feet per second and a flat operating characteristics at constant speed has been designed and tested. It was designed for a constant power input per pound of flow in expectation that this would result in a wider mass-flow operating range at a given stagnation-presssure ratio. The design specific weight flow was 21.3 pounds per second per square foot of frontal area at atmospheric discharge with a stagnation-pressure ratio of 3.25 and an inlet hub-tip radius ratio of 0.7. Several configurations consisting of various blade setting angles and solidities were tested. Tests showed that the design flow, pressure ratio, and flat operating characteristic were obtained over a range of 10 percent of design flow at a peak efficiency of 82 percent for design conditions. The compressor had a possible immediate application for air removal from a large slotted-throat transonic wind tunnel, but the design theory could apply to any low-speed industrial compressor or second spool of a turbojet engine.

Annual Report Of The National Advisory Committee For Aeronautics

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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1958

Annual Report Of The National Advisory Committee For Aeronautics written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with Aeronautics categories.

Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.

Report

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Author :
language : en
Publisher:
Release Date : 1953

Report written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Aeronautics categories.

Research Abstracts And Reclassification Notice

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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1956

Research Abstracts And Reclassification Notice written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Aeronautics categories.

Technical Note National Advisory Committee For Aeronautics

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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1958

Technical Note National Advisory Committee For Aeronautics written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with Aeronautics categories.

Flutter Analysis Of Rectangular Wings Of Very Low Aspect Ratio

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Author : Robert William Fralich
language : en
Publisher:
Release Date : 1958

Flutter Analysis Of Rectangular Wings Of Very Low Aspect Ratio written by Robert William Fralich and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with Aerofoils categories.

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.