Download or read book Design of Axisymmetric Exhaust Nozzles by Method of Characteristics Incorporating a Variable Isentropic Exponent written by Eleanor Costilow Guentert and published by . This book was released on 1959 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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:

Download or read book Internal Performance Characteristics of Short Convergent divergent Exhaust Nozzles Designed by the Method of Characteristics written by H. George Krull and published by . This book was released on 1956 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: An evaluation of the internal performance characteristics of short nozzles designed by the method of characteristics was obtained over a range of nozzle pressure ratios from 1.5 to 22.

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 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design of Axisymmetric Exhaust Nozzles by Method of Characteristics Incorporating a Variable Isentropic Exponent written by Eleanor Costilow Guentert and published by . This book was released on 1959 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical method for including thermodynamic data with variable isentropic exponent in the method of characteristics as applied to the design of high-temperature exhaust nozzles has been obtained. Several bell-shaped nozzles have been designed with this method. A comparison of nozzle contours obtained by assuming identical boundary conditions and either frozen or equilibrium composition shows that significant differences occur. A computation of the variation of vacuum specific impulse with axial length showed that considerable nozzle length, and hence weight, can be eliminated without serious thrust penalties in nozzle designs that gradually expand the flow to uniform exit conditions.

Download or read book Jet engine Exhaust Noise from Slot Nozzles written by Willard D. Coles and published by . This book was released on 1959 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design of Axisymmetric Exhaust Nozzles by Method of Characteristics Incorporating a Variable Isentropic Exponent written by Harvey E.. Neumann and published by . This book was released on 1959 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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:

Download or read book Acoustics and Trust of Separate Flow Exhaust Nozzles With Mixing Devices for High Bypass Ratio Engines written by and published by . This book was released on 2000 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Pitot Survey of Exhaust Flow Field of a 2 D Scramjet Nozzle at Mach 6 with Air Or Freon and Argon Used for Exhaust Simulation written by William J. Monta and published by . This book was released on 1992 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Performance Evaluation of Fixed and Variable area Rocket Exhaust Diffusers Using Single and Clustered Nozzles with and Without Gimbaling written by Bruce E. Church and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

Download or read book Performance of Several Method of characteristics Exhaust Nozzles written by John M. Farley and published by . This book was released on 1960 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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

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

Download or read book Noise Evaluation of Four Exhaust Nozzles for Afterburning Turbojet Engine written by George V. Darchuk and published by . This book was released on 1970 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Comparison of Predicted and Experimental Wall Temperatures for a Cylindrical Ejector Exhaust Nozzle Operated with a Turbojet Gas Generator written by Arthur Lieberman and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The shroud wall temperatures during operation with and without an afterburner are predicted analytically by using a wall heat balance of hot gas radiation, coolant convection, internal and external radiation, and external free convection. The Hatch-Papell film-cooling correlation predicts an adiabatic wall temperature which is used as the driving temperature for the coolant heat transfer. Ejectors with nozzle area ratios from 1.65 to 2. 75 and ejector length to primary diameter ratios from 1.63 to 1.95 were tested. Tests were conducted at nozzle pressure ratios ranging from 2.0 to 6.3, primary total temperatures from 861 to 1939 K (1550 [degree] to 3490 [degree] R), and corrected secondary weight-flow ratios from 0.027 to 0.088. The predictions yielded reasonably good results throughout the range of conditions tested.