Workshop On Thrust Augmenting Ejectors

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Workshop On Thrust Augmenting Ejectors

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Author :
language : en
Publisher:
Release Date : 1979

Workshop On Thrust Augmenting Ejectors written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1979 with Airplanes categories.

Workshop On Thrust Augmenting Ejectors

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Author : D. G. Koenig
language : en
Publisher:
Release Date : 1979

Workshop On Thrust Augmenting Ejectors written by D. G. Koenig and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1979 with categories.

Thrust Augmenting Ejectors

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Author : NASA. Ames Research Center
language : en
Publisher:
Release Date :

Thrust Augmenting Ejectors written by NASA. Ames Research Center and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on with categories.

Proceedings

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Author : R. P. Braden
language : en
Publisher:
Release Date : 1982

Proceedings written by R. P. Braden and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1982 with Short take-off and landing aircraft categories.

Thrust Augmenting Ejectors

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Author : Viets, Hermann
language : en
Publisher:
Release Date : 1975

Thrust Augmenting Ejectors written by Viets, Hermann and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Ejector pumps categories.

Thrust Augmenting Ejectors

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Author : K. S. Nagaraja
language : en
Publisher:
Release Date : 1993

Thrust Augmenting Ejectors written by K. S. Nagaraja and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1993 with categories.

Thrust Augmenting Ejectors

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Author : Morton Alperin
language : en
Publisher:
Release Date : 1981

Thrust Augmenting Ejectors written by Morton Alperin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with categories.

A discussion of the development of the compact jet-diffuser ejectors utilized for hovering and low speed flight propulsion has been presented. This is followed by a description of ideal ejector performance as derived from a compressible flow theory, over the range of flight speeds from zero to supersonic speed. These analyses introduced the concepts of ejector configuration optimization and the validity of the so-called 'second solution' to the mixing problem, wherein the flow after complete mixing is supersonic. The ideal performance of thrust augmenting ejectors designed under this 'second solution' has been shown to be far superior to those designed by conventional methods. The ability of properly designed ejectors to utilize the thermal energy of injected gas for the production of useful energy has also been described. Finally, the influence of major losses has been discussed, including means for avoiding excessive performance degradation by proper optimization of the geometry of the ejector in view of these losses.

Scientific And Technical Aerospace Reports

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Author :
language : en
Publisher:
Release Date : 1992

Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1992 with Aeronautics categories.

Experimental Investigation Of High Performance Short Thrust Augmenting Ejectors

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Author :
language : en
Publisher:
Release Date : 1983

Experimental Investigation Of High Performance Short Thrust Augmenting Ejectors written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1983 with categories.

Results of an experimental investigation concerning the design and testing of air-to-air thrust augmenting ejectors utilizing short curved-wall diffusers are presented. These ejectors were designed primarily according to the procedure established in an analytical research effort sponsored by DTNSRDC from 1980-1981. Two of the three ejectors tested have identical mixing chambers. The mixing chamber inlet area to the primary nozzle area ratio lambda was 40. The overall ejector length-to-mixing chamber diameter ratios L/D(overall) were 6.09 and 6.16; diffuser area ratios AR(diff) were 1.33 and 1.46, respectively. The third ejector had an L/D(overall) of 6.02, a lambda of 20 and an AR(diff) of 1. 26. The best observed thrust augmentation ratio phi and the modified thrust augmentation ratio phi sub 2 were 2.11 and 1.91 respectively for a sonic primary jet. The modified thrust augmentation ratio phi sub 2 accounts for the penalty of suction in preventing flow separation in the diffuser. These levels of thrust ratio were derived from velocity measurements at the ejector exit. Independent thrust measurements obtained with strain gages on the mixing chamber agree with the force calculated from the momentum data. The experimentally observed ejector performance data correlated well with the predicted values. (Author).

Inlet And Diffuser Effects On Thrust Augmenting Ejectors

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Author : S. G. Reznick
language : en
Publisher:
Release Date : 1982

Inlet And Diffuser Effects On Thrust Augmenting Ejectors written by S. G. Reznick and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1982 with categories.

Effects of primary jet inlet nozzle configuration and diffuser geometry on the thrust augmentation of circular and rectangular ejectors are investigated in an experimental study. The rectangular ejector inlet nozzle configurations consist of either one, two, or three slot nozzles. The circular ejector inlet nozzles consist of slot nozzles placed either across the inlet or around the inlet periphery. Diffuser geometry is varied primarily by changing the diffuser area ratio. Effect on thrust performance of the primary flow injection angle relative to the inlet walls is investigated. Effects of side-wall, end-wall, and diffuser blowing on thrust performance and diffuser stall also are considered.