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Author : Leonard E. Stitt
Publisher :
ISBN 13 :
Total Pages : 118 pages
Book Rating : 4.F/5 ( download)
Download or read book Exhaust Nozzles for Propulsion Systems with Emphasis on Supersonic Cruise Aircraft written by Leonard E. Stitt and published by . This book was released on 1990 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Gregory M. Buck
Publisher : BiblioGov
ISBN 13 : 9781289251161
Total Pages : 398 pages
Book Rating : 4.2/5 (511 download)
Download or read book Critical Propulsion Components written by Gregory M. Buck and published by BiblioGov. This book was released on 2013-07 with total page 398 pages. Available in PDF, EPUB and Kindle. Book excerpt: Several studies have concluded that a supersonic aircraft, if environmentally acceptable and economically viable, could successfully compete in the 21st century marketplace. However, before industry can commit to what is estimated as a 15 to 20 billion dollar investment, several barrier issues must be resolved. In an effort to address these barrier issues, NASA and Industry teamed to form the High-Speed Research (HSR) program. As part of this program, the Critical Propulsion Components (CPC) element was created and assigned the task of developing those propulsion component technologies necessary to: (1) reduce cruise emissions by a factor of 10 and (2) meet the ever-increasing airport noise restrictions with an economically viable propulsion system. The CPC-identified critical components were ultra-low emission combustors, low-noise/high-performance exhaust nozzles, low-noise fans, and stable/high-performance inlets. Propulsion cycle studies (coordinated with NASA Langley Research Center sponsored airplane studies) were conducted throughout this CPC program to help evaluate candidate components and select the best concepts for the more complex and larger scale research efforts. The propulsion cycle and components ultimately selected were a mixed-flow turbofan (MFTF) engine employing a lean, premixed, prevaporized (LPP) combustor coupled to a two-dimensional mixed compression inlet and a two-dimensional mixer/ejector nozzle. Due to the large amount of material presented in this report, it was prepared in four volumes; Volume 1: Summary, Introduction, and Propulsion System Studies, Volume 2: Combustor, Volume 3: Exhaust Nozzle, and Volume 4: Inlet and Fan/Inlet Acoustic Team.
Author :
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (317 download)
Download or read book Flight and Wind Tunnel Investigation of Installation Effects on Underwing Supersonic Cruise Exhaust Nozzles at Transonic Speeds written by and published by . This book was released on 1970 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721983704
Total Pages : 394 pages
Book Rating : 4.9/5 (837 download)
Download or read book Critical Propulsion Components. Volume 3; Exhaust Nozzle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-28 with total page 394 pages. Available in PDF, EPUB and Kindle. Book excerpt: Several studies have concluded that a supersonic aircraft, if environmentally acceptable and economically viable, could successfully compete in the 21st century marketplace. However, before industry can commit to what is estimated as a 15 to 20 billion dollar investment, several barrier issues must be resolved. In an effort to address these barrier issues, NASA and Industry teamed to form the High-Speed Research (HSR) program. As part of this program, the Critical Propulsion Components (CPC) element was created and assigned the task of developing those propulsion component technologies necessary to: (1) reduce cruise emissions by a factor of 10 and (2) meet the ever-increasing airport noise restrictions with an economically viable propulsion system. The CPC-identified critical components were ultra-low emission combustors, low-noise/high-performance exhaust nozzles, low-noise fans, and stable/high-performance inlets. Propulsion cycle studies (coordinated with NASA Langley Research Center sponsored airplane studies) were conducted throughout this CPC program to help evaluate candidate components and select the best concepts for the more complex and larger scale research efforts. The propulsion cycle and components ultimately selected were a mixed-flow turbofan (MFTF) engine employing a lean, premixed, prevaporized (LPP) combustor coupled to a two-dimensional mixed compression inlet and a two-dimensional mixer/ejector nozzle. Due to the large amount of material presented in this report, it was prepared in four volumes; Volume 1: Summary, Introduction, and Propulsion System Studies, Volume 2: Combustor, Volume 3: Exhaust Nozzle, and Volume 4: Inlet and Fan/Inlet Acoustic Team. Glenn Research Center NAS3-27235; WBS 22-714-09-47...
Author :
Publisher :
ISBN 13 :
Total Pages : 116 pages
Book Rating : 4.3/5 (243 download)
Download or read book NASA Reference Publication written by and published by . This book was released on 1977 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721531660
Total Pages : 26 pages
Book Rating : 4.5/5 (316 download)
Download or read book A Survey of Challenges in Aerodynamic Exhaust Nozzle Technology for Aerospace Propulsion Applications written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-20 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The current paper discusses aerodynamic exhaust nozzle technology challenges for aircraft and space propulsion systems. Technology advances in computational and experimental methods have led to more accurate design and analysis tools, but many major challenges continue to exist in nozzle performance, jet noise and weight reduction. New generations of aircraft and space vehicle concepts dictate that exhaust nozzles have optimum performance, low weight and acceptable noise signatures. Numerous innovative nozzle concepts have been proposed for advanced subsonic, supersonic and hypersonic vehicle configurations such as ejector, mixer-ejector, plug, single expansion ramp, altitude compensating, lobed and chevron nozzles. This paper will discuss the technology barriers that exist for exhaust nozzles as well as current research efforts in place to address the barriers. Shyne, Rickey J. Glenn Research Center NASA/TM-2002-211977, NAS 1.15:211977, E-13646
Author : Fred A. Wilcox
Publisher :
ISBN 13 :
Total Pages : 6 pages
Book Rating : 4.:/5 (455 download)
Download or read book Flight and Wind Tunnel Investigation of Installation Effects on Supersonic Cruise Exhaust Nozzles at Transonic Speeds written by Fred A. Wilcox and published by . This book was released on 1969 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : G. R. Nickerson
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Optimized Supersonic Exhaust Nozzles for Hypersonic Propulsion written by G. R. Nickerson and published by . This book was released on 1988 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722272609
Total Pages : 26 pages
Book Rating : 4.2/5 (726 download)
Download or read book High Speed Nozzles Task written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-05 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic cruise exhaust nozzles for advanced applications are optimized for a high nozzle pressure ratio (NPR) at design supersonic cruise Mach number and altitude. The performance of these nozzles with large expansion ratios are severely degraded for operations at subsonic speeds near sea level for NPR significantly less than the design values. The prediction of over-expanded 2DCD nozzles performance is critical to evaluating the internal losses and to the optimization of the integrated vehicle and propulsion system performance. The reported research work was aimed at validating and assessing existing computational methods and turbulence models for predicting the flow characteristics and nozzle performance at over-expanded conditions. Flow simulations in 2DCD nozzles were performed using five different turbulence models. The results are compared with the experimental data for the wall pressure distribution and thrust and flow coefficients at over-expanded static conditions. Hamed, Awatef Unspecified Center OAI-120520...
Author : Lawrence L. Galigher
Publisher :
ISBN 13 :
Total Pages : 128 pages
Book Rating : 4.3/5 (91 download)
Download or read book Evaluation of Various Exhaust Nozzles at Free-stream Mach Numbers from 0.6 To. 3.0 written by Lawrence L. Galigher and published by . This book was released on 1970 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 50 pages
Book Rating : 4.:/5 (317 download)
Download or read book Supersonic Investigation of Two Dimensional Hypersonic Exhaust Nozzles written by and published by . This book was released on 1992 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Andrew Gelsey
Publisher :
ISBN 13 :
Total Pages : 18 pages
Book Rating : 4.:/5 (358 download)
Download or read book A Computational Environment for Exhaust Nozzle Design written by Andrew Gelsey and published by . This book was released on 1995 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: "The Nozzle Design Associate (NDA) is a computational environment for the design of jet engine exhaust nozzles for supersonic aircraft. NDA may be used either to design new aircraft or to design new nozzles that adapt existing aircraft so they may be reutilized for new missions. NDA was developed in a collaboration between computer scientists at Rutgers University and exhaust nozzle designers at General Electric Aircraft Engines and General Electric Corporate Research and Development. The NDA project has two principle goals: to provide a useful engineering tool for exhaust nozzle design, and to explore fundamental research issues that arise in the application of automated design optimization methods to realistic engineering problems."
Author : E. B. Thayer
Publisher : BiblioGov
ISBN 13 : 9781289261412
Total Pages : 196 pages
Book Rating : 4.2/5 (614 download)
Download or read book Generation 1. 5 High Speed Civil Transport Exhaust Nozzle Program written by E. B. Thayer and published by BiblioGov. This book was released on 2013-07 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this program was to conduct an experimental and analytical evaluation of low noise exhaust nozzles suitable for future High-Speed Civil Transport (HSCT) aircraft. The experimental portion of the program involved parametric subscale performance model tests of mixer/ejector nozzles in the takeoff mode, and high-speed tests of mixer/ejectors converted to two-dimensional convergent-divergent (2-D/C-D), plug, and single expansion ramp nozzles (SERN) in the cruise mode. Mixer/ejector results show measured static thrust coefficients at secondary flow entrainment levels of 70 percent of primary flow. Results of the high-speed performance tests showed that relatively long, straight-wall, C-D nozzles could meet supersonic cruise thrust coefficient goal of 0.982; but the plug, ramp, and shorter C-D nozzles required isentropic contours to reach the same level of performance. The computational fluid dynamic (CFD) study accurately predicted mixer/ejector pressure distributions and shock locations. Heat transfer studies showed that a combination of insulation and convective cooling was more effective than film cooling for nonafterburning, low-noise nozzles. The thrust augmentation study indicated potential benefits for use of ejector nozzles in the subsonic cruise mode if the ejector inlet contains a sonic throat plane.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721983858
Total Pages : 330 pages
Book Rating : 4.9/5 (838 download)
Download or read book Critical Propulsion Components. Volume 1; Summary, Introduction, and Propulsion Systems Studies written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-28 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt: Several studies have concluded that a supersonic aircraft, if environmentally acceptable and economically viable, could successfully compete in the 21st century marketplace. However, before industry can commit to what is estimated as a 15 to 20 billion dollar investment, several barrier issues must be resolved. In an effort to address these barrier issues, NASA and Industry teamed to form the High-Speed Research (HSR) program. As part of this program, the Critical Propulsion Components (CPC) element was created and assigned the task of developing those propulsion component technologies necessary to: (1) reduce cruise emissions by a factor of 10 and (2) meet the ever-increasing airport noise restrictions with an economically viable propulsion system. The CPC-identified critical components were ultra-low emission combustors, low-noise/high-performance exhaust nozzles, low-noise fans, and stable/high-performance inlets. Propulsion cycle studies (coordinated with NASA Langley Research Center sponsored airplane studies) were conducted throughout this CPC program to help evaluate candidate components and select the best concepts for the more complex and larger scale research efforts. The propulsion cycle and components ultimately selected were a mixed-flow turbofan (MFTF) engine employing a lean, premixed, prevaporized (LPP) combustor coupled to a two-dimensional mixed compression inlet and a two-dimensional mixer/ejector nozzle. Due to the large amount of material presented in this report, it was prepared in four volumes; Volume 1: Summary, Introduction, and Propulsion System Studies, Volume 2: Combustor, Volume 3: Exhaust Nozzle, and Volume 4: Inlet and Fan/ Inlet Acoustic Team. Glenn Research Center NAS3-27235; WBS 22-714-09...
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722830243
Total Pages : 46 pages
Book Rating : 4.8/5 (32 download)
Download or read book Supersonic Investigation of Two Dimensional Hypersonic Exhaust Nozzles written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-12 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the NASA Lewis 10 x 10 ft supersonic Wind Tunnel to determine the performance characteristics of 2D hypersonic exhaust nozzles/afterbodies at low supersonic conditions. Generally, this type of application requires a single expansion ramp nozzle (SERN) that is highly integrated with the airframe of the hypersonic vehicle. At design conditions (hypersonic speeds), the nozzle generally exhibits acceptable performance. At off-design conditions (transonic to mid-supersonic speeds), nozzle performance of a fixed geometry configuration is generally poor. Various 2-D nozzle configurations were tested at off-design conditions from Mach 2.0 to 3.5. Performance data is presented at nozzle pressure ratios from 1 to 35. Jet exhaust was simulated with high-pressure air. To study performance of different geometries, nozzle configurations were varied by interchanging the following model parts: internal upstream contour, expansion ramp, sidewalls, and cowl. Carboni, Jeanne D. and Shyne, Rickey J. and Leavitt, Laurence D. and Taylor, John G. and Lamb, Milton Glenn Research Center; Langley Research Center RTOP 763-01-21...
Author : Bobby L. Berrier
Publisher :
ISBN 13 :
Total Pages : 228 pages
Book Rating : 4.:/5 (31 download)
Download or read book Investigation of Convergent-divergent Nozzles Applicable to Reduced-power Supersonic Cruise Aircraft written by Bobby L. Berrier and published by . This book was released on 1980 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721142989
Total Pages : 192 pages
Book Rating : 4.1/5 (429 download)
Download or read book Generation 1.5 High Speed Civil Transport (Hsct) Exhaust Nozzle Program written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this program was to conduct an experimental and analytical evaluation of low noise exhaust nozzles suitable for future High-Speed Civil Transport (HSCT) aircraft. The experimental portion of the program involved parametric subscale performance model tests of mixer/ejector nozzles in the takeoff mode, and high-speed tests of mixer/ejectors converted to two-dimensional convergent-divergent (2-D/C-D), plug, and single expansion ramp nozzles (SERN) in the cruise mode. Mixer/ejector results show measured static thrust coefficients at secondary flow entrainment levels of 70 percent of primary flow. Results of the high-speed performance tests showed that relatively long, straight-wall, C-D nozzles could meet supersonic cruise thrust coefficient goal of 0.982; but the plug, ramp, and shorter C-D nozzles required isentropic contours to reach the same level of performance. The computational fluid dynamic (CFD) study accurately predicted mixer/ejector pressure distributions and shock locations. Heat transfer studies showed that a combination of insulation and convective cooling was more effective than film cooling for nonafterburning, low-noise nozzles. The thrust augmentation study indicated potential benefits for use of ejector nozzles in the subsonic cruise mode if the ejector inlet contains a sonic throat plane. Thayer, E. B. and Gamble, E. J. and Guthrie, A. R. and Kehret, D. F. and Barber, T. J. and Hendricks, G. J. and Nagaraja, K. S. and Minardi, J. E. Glenn Research Center NAS3-26618; WBS 22-714-09-46
