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Exhaust Plume Thermodynamic Effects On Nonaxisymmetric Nozzle Afterbody Performance In Transonic Flow
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Book Synopsis Exhaust Plume Thermodynamic Effects on Nonaxisymmetric Nozzle Afterbody Performance in Transonic Flow by : C. E. Robinson
Download or read book Exhaust Plume Thermodynamic Effects on Nonaxisymmetric Nozzle Afterbody Performance in Transonic Flow written by C. E. Robinson and published by . This book was released on 1978 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the effect of exhaust plume thermodynamic properties on a nonaxisymmetric nozzle afterbody. The model consisted of a strut-mounted cone-cylinder with an isolated nozzle afterbody. The shape of the nozzle afterbody was generally based on the early configurations of the ADEN design. An ethylene/air combustor was used to vary the thermodynamic properties by varying fuel-to-air ratio. Data were obtained at four fuel-to-air ratios representing exhaust plume temperatures of approximately 500 F (cold flow, fuel-to-air = 0), 1,200, 1,500, and 1,900 R. Pressure measurements of the nozzle afterbody surface were obtained from which drag coefficients along the rows of pressure orifices were calculated. The investigation was conducted over a range of Mach numbers from 0.6 to 1.4 at a Reynolds number per foot of 2.5 million. Generally, the nozzle afterbody drag decreased with increasing exhaust plume temperature over the entire Mach number range.
Book Synopsis Exhaust Plume Thermodynamic Effects on Nonaxisymmetric Nozzle Afterbody Performance in Transonic Flow by :
Download or read book Exhaust Plume Thermodynamic Effects on Nonaxisymmetric Nozzle Afterbody Performance in Transonic Flow written by and published by . This book was released on 1978 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the effect of exhaust plume thermodynamic properties on a nonaxisymmetric nozzle afterbody. The model consisted of a strut-mounted cone-cylinder with an isolated nozzle afterbody. The shape of the nozzle afterbody was generally based on the early configurations of the ADEN design. An ethylene/air combustor was used to vary the thermodynamic properties by varying fuel-to-air ratio. Data were obtained at four fuel-to-air ratios representing exhaust plume temperatures of approximately 500 F (cold flow, fuel-to-air = 0), 1,200, 1,500, and 1,900 R. Pressure measurements of the nozzle afterbody surface were obtained from which drag coefficients along the rows of pressure orifices were calculated. The investigation was conducted over a range of Mach numbers from 0.6 to 1.4 at a Reynolds number per foot of 2.5 million. Generally, the nozzle afterbody drag decreased with increasing exhaust plume temperature over the entire Mach number range.
Book Synopsis Vectored Propulsion, Supermaneuverability and Robot Aircraft by : Benjamin Gal-Or
Download or read book Vectored Propulsion, Supermaneuverability and Robot Aircraft written by Benjamin Gal-Or and published by Springer Science & Business Media. This book was released on 2013-11-09 with total page 277 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is designed to fill a professional vacuum in the new field of advance, high-angle, vectored stealth aircraft. The subject matter presented in the volume has never before been investigated and presented as a unified field of study because it covers entirely new fields and because specialized fragments of this unified field are scattered throughout literature in specific problems. The book is of interest to aeronautical and mechanical engineers, electrical and control engineers, aerospace industry, USAF, US Navy, NASA, pilots and instructors.
Book Synopsis Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range by :
Download or read book Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range written by and published by . This book was released on 1974 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an experimental and analytical research investigation on nozzle/afterbody drag are presented. Experimental afterbody (and boattail) drag coefficients and pressure distributions are discussed for an isolated, strut-mounted nozzle/afterbody model for the Mach number range from 0.6 to 1.5. Some data are also given for free-stream unit Reynolds numbers from one million to approximately four million per foot. The experimental data were obtained for the basic model with an air-cooled and a water-cooled Ethylene/air combustor to provide hot-jet duplication as well as cold-jet simulation. The temperature of the nozzle exhaust gas was varied from 530R (burner-off) to approximately 2500R for several nozzle pressure ratios from jet-off to those corresponding to a moderately under-expanded exhaust plum. The initial series of experiments was conducted with the air-cooled combustors, and the effect of jet temperature on afterbody drag was somewhat masked by the effects of the secondary airflow from the cooling air. The general trend, however, shows a decreasing afterbody drag with increasing exhaust gas temperature and with decreasing secondary airflow at a fixed nozzle pressure ratio. (Modified author abstract).
Book Synopsis Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range by :
Download or read book Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range written by and published by . This book was released on 1974 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an experimental and analytical research investigation on nozzle/afterbody drag are presented. Experimental afterbody (and boattail) drag coefficients and pressure distributions are discussed for an isolated, strut-mounted nozzle/afterbody model for the Mach number range from 0.6 to 1.5. Some data are also given for free-stream unit Reynolds numbers from one million to approximately four million per foot. The experimental data were obtained for the basic model with an air-cooled and a water-cooled Ethylene/air combustor to provide hot-jet duplication as well as cold-jet simulation. The temperature of the nozzle exhaust gas was varied from 530R (burner-off) to approximately 2500R for several nozzle pressure ratios from jet-off to those corresponding to a moderately under-expanded exhaust plum. The initial series of experiments was conducted with the air-cooled combustors, and the effect of jet temperature on afterbody drag was somewhat masked by the effects of the secondary airflow from the cooling air. The general trend, however, shows a decreasing afterbody drag with increasing exhaust gas temperature and with decreasing secondary airflow at a fixed nozzle pressure ratio. (Modified author abstract).
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1979 with total page 722 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author :North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development Publisher : ISBN 13 : Total Pages :542 pages Book Rating :4.3/5 (243 download)
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Book Synopsis Effects of Convoluted Divergent Flap Contouring on the Performance of a Fixed-Geometry Nonaxisymmetric Exhaust Nozzle by : Scott C. Asbury
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Book Synopsis Effect of Afterbody Terminal Fairings on the Performance of Plug-type Exhaust Nozzles at Transonic Speeds by :
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