Jet-diffuser Ejector - Attached Nozzle Design PDF Download
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Author:
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Category :
Languages : en
Pages : 84
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Book Description
Author:
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ISBN:
Category :
Languages : en
Pages : 84
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Author:
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Category : Airplanes
Languages : en
Pages : 524
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Author:
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Category : Aeronautics
Languages : en
Pages : 692
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Author: James W. Hale
Publisher:
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Category :
Languages : en
Pages : 65
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Book Description
An investigation was conducted to determine the best shape for a diffuser-ejector configuration for a two-nozzle cluster rocket and included the performance of various combinations of configurations derived from six basic diffuser-ejector geometric shapes and sizes and four basic arrangements of nozzle configurations. The performance was obtained for all configurations both with and without ejected mass from the test cell. The ejected mass from the test cell was accomplished by two parallel auxiliary jet pumps. The simulated rocket nozzles were conical 13.25-deg half angle. Unheated dry air was used as the driving fluid for the simulated rocket and jet pumps. Saturated 200-psig steam was also used as a jet pump driving fluid.
Author: Morton Alperin
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition to conventional flight was to be achieved by a unique system consisting of vector control jets and a diffuser flap. This system was intended to provide a rearward deflection of the effluent flow and a corresponding thrust force in the flight direction. A single ejector equipped with only one vector control jet and a diffuser flap was installed close to the leading edge of the strake of a one-fifth scale, semi-span model of the aircraft, without wing, canard or tail surface. Tests of the system at a nozzle pressure ratio of 1.24 indicated a thrust augmentation of 1.92 and a thrust in the flight direction of about 12% of the total thrust under static conditions. An ejector stall occurred at a ratio of tunnel dynamic pressure to nozzle gage pressure of about 0.008. Ejector stall speed can be delayed by using a boundary layer control jet at the front inlet lip of the ejector. (Author).
Author:
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Category : Aeronautics
Languages : en
Pages : 654
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Author: Richard A. Yeager
Publisher:
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Category :
Languages : en
Pages : 16
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Author: R. P. Braden
Publisher:
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Category : Short take-off and landing aircraft
Languages : en
Pages : 1094
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Book Description
Author: Ajoy Kumar
Publisher: Alpha Science Int'l Ltd.
ISBN: 9781842650912
Category : Technology & Engineering
Languages : en
Pages : 716
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Book Description
This work covers in a comprehensive and coherent manner, fundamentals of thermodynamics and their engineering applications. Beginning with elementary ideas of pressure, temperature and heat it develops the laws of thermodynamics from experimental and engineering backgrounds.
Author: Vishwas G. Pangarkar
Publisher: John Wiley & Sons
ISBN: 1118807561
Category : Technology & Engineering
Languages : en
Pages : 532
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Book Description
Details simple design methods for multiphase reactors in the chemical process industries Includes basic aspects of transport in multiphase reactors and the importance of relatively reliable and simple procedures for predicting mass transfer parameters Details of design and scale up aspects of several important types of multiphase reactors Examples illustrated through design methodologies presenting different reactors for reactions that are industrially important Includes simple spreadsheet packages rather than complex algorithms / programs or computational aid
