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Exhaust Nozzle Plume And Shock Wave Interaction
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781719392037 Total Pages :26 pages Book Rating :4.3/5 (92 download)
Book Synopsis Exhaust Nozzle Plume and Shock Wave Interaction by : National Aeronautics and Space Administration (NASA)
Download or read book Exhaust Nozzle Plume and Shock Wave Interaction written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Fundamental research for sonic boom reduction is needed to quantify the interaction of shock waves generated from the aircraft wing or tail surfaces with the exhaust plume. Both the nozzle exhaust plume shape and the tail shock shape may be affected by an interaction that may alter the vehicle sonic boom signature. The plume and shock interaction was studied using Computational Fluid Dynamics simulation on two types of convergent-divergent nozzles and a simple wedge shock generator. The nozzle plume effects on the lower wedge compression region are evaluated for two- and three-dimensional nozzle plumes. Results show that the compression from the wedge deflects the nozzle plume and shocks form on the deflected lower plume boundary. The sonic boom pressure signature of the wedge is modified by the presence of the plume, and the computational predictions show significant (8 to 15 percent) changes in shock amplitude. Castner, Raymond S. and Elmiligui, Alaa and Cliff, Susan Ames Research Center; Glenn Research Center; Langley Research Center COMPUTATIONAL FLUID DYNAMICS; EXHAUST NOZZLES; SHOCK WAVE INTERACTION; PLUMES; EXHAUST GASES; CONVERGENT-DIVERGENT NOZZLES; SONIC BOOMS; TAIL SURFACES; DEFLECTION; BOUNDARIES
Book Synopsis Exhaust nozzle plume and shock wave interaction by : Raymond S. Castner
Download or read book Exhaust nozzle plume and shock wave interaction written by Raymond S. Castner and published by . This book was released on 2013 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles by : Nasa Technical Reports Server (Ntrs)
Download or read book Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reducing or eliminating the operational restrictions of supersonic aircraft over populated areas has led to extensive research at NASA. Restrictions were due to the disturbance of the sonic boom, caused by the coalescence of shock waves formed off the aircraft. Recent work has been performed to reduce the magnitude of the sonic boom N-wave generated by airplane components with focus on shock waves caused by the exhaust nozzle plume. Previous Computational Fluid Dynamics (CFD) analysis showed how the shock wave formed at the nozzle lip interacts with the nozzle boat-tail expansion wave. An experiment was conducted in the 1- by 1-ft Supersonic Wind Tunnel at the NASA Glenn Research Center to validate the computational study. Results demonstrated how the nozzle lip shock moved with increasing nozzle pressure ratio (NPR) and reduced the nozzle boat-tail expansion, causing a favorable change in the observed pressure signature. Experimental results were presented for comparison to the CFD results. The strong nozzle lip shock at high values of NPR intersected the nozzle boat-tail expansion and suppressed the expansion wave. Based on these results, it may be feasible to reduce the boat-tail expansion for a future supersonic aircraft with under-expanded nozzle exhaust flow by modifying nozzle pressure or nozzle divergent section geometry.
Book Synopsis Turbulent Shear-Layer/Shock-Wave Interactions by : J. Delery
Download or read book Turbulent Shear-Layer/Shock-Wave Interactions written by J. Delery and published by Springer Science & Business Media. This book was released on 2013-03-08 with total page 434 pages. Available in PDF, EPUB and Kindle. Book excerpt: It was on a proposal of the late Professor Maurice Roy, member of the French Academy of Sciences, that in 1982, the General Assembly of the International Union of Theoretical and Applied Mechanics decided to sponsor a symposium on Turbulent Shear-Layer/Shock-Wave Interactions. This sympo sium might be arranged in Paris -or in its immediate vicinity-during the year 1985. Upon request of Professor Robert Legendre, member of the French Academy of Sciences, the organization of the symposium might be provided by the Office National d'Etudes et de Recherches Aerospatiales (ONERA). The request was very favorably received by Monsieur l'Ingenieur General Andre Auriol, then General Director of ONERA. The subject of interactions between shock-waves and turbulent dissipative layers is of considerable importance for many practical devices and has a wide range of engineering applications. Such phenomena occur almost inevitably in any transonic or supersonic flow and the subject has given rise to an important research effort since the advent of high speed fluid mechanics, more than forty years ago. However, with the coming of age of modern computers and the development of new sophisticated measurement techniques, considerable progress has been made in the field over the past fifteen years. The aim of the symposium was to provide an updated status of the research effort devoted to shear layer/shock-wave interactions and to present the most significant results obtained recently.
Book Synopsis The Effect of Exhaust Plume/afterbody Interaction on Installed Scramjet Performance by : Thomas Alan Edwards
Download or read book The Effect of Exhaust Plume/afterbody Interaction on Installed Scramjet Performance written by Thomas Alan Edwards and published by . This book was released on 1988 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transient Shock Wave Interaction with Rocket Nozzle by : H. S. Chopra
Download or read book Transient Shock Wave Interaction with Rocket Nozzle written by H. S. Chopra and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Improved Interaction Method for Calculating Exhaust Nozzle Boattail Flows by :
Download or read book An Improved Interaction Method for Calculating Exhaust Nozzle Boattail Flows written by and published by . This book was released on 1980 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A turbulent boundary-layer, inviscid flow interaction method for calculating axisymmetric nozzle boattail configurations is presented. The method is applicable to flows with subsonic or supersonic free streams with Mach number in the range 0.5 - 1.5, including flows with shock-wave induced separation and to bodies with either high pressure exhaust plumes or solid plume simulators. The theory and some sample calculations are presented along with detailed instructions for preparation of input data, description of output, and instructions for operation of the computer program on an IBM 370 computer. (Author).
Book Synopsis Turbulent Shear-layer/shock-wave Interactions by :
Download or read book Turbulent Shear-layer/shock-wave Interactions written by and published by . This book was released on 1986 with total page 466 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Improved Interaction Method for Calculating Exhaust Nozzle Boattail Flows by :
Download or read book An Improved Interaction Method for Calculating Exhaust Nozzle Boattail Flows written by and published by . This book was released on 1980 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A turbulent boundary-layer, inviscid flow interaction method for calculating axisymmetric nozzle boattail configurations is presented. The method is applicable to flows with subsonic or supersonic free streams with Mach number in the range 0.5 - 1.5, including flows with shock-wave induced separation and to bodies with either high pressure exhaust plumes or solid plume simulators. The theory and some sample calculations are presented along with detailed instructions for preparation of input data, description of output, and instructions for operation of the computer program on an IBM 370 computer. (Author).
Book Synopsis Nozzle Plume/shock Interaction Experimental and Computational Sonic Boom Analyses from the NASA Ames 9-by 7-foot Supersonic Wind Tunnel by : D. A. Durston
Download or read book Nozzle Plume/shock Interaction Experimental and Computational Sonic Boom Analyses from the NASA Ames 9-by 7-foot Supersonic Wind Tunnel written by D. A. Durston and published by . This book was released on 2018 with total page 489 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings by : Song Fu
Download or read book 2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings written by Song Fu and published by Springer Nature. This book was released on with total page 1991 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1995 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit July 20-23, 2003, Huntsville, Alabama: 03-4400 - 03-4449 by :
Download or read book 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit July 20-23, 2003, Huntsville, Alabama: 03-4400 - 03-4449 written by and published by . This book was released on 2003 with total page 526 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1972 with total page 520 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles by : Raymond S. Castner
Download or read book Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles written by Raymond S. Castner and published by . This book was released on 2011 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Performance of a Fixed-Geometry Exhaust Nozzle Incorporating Porous Cavities for Shock-Boundary Layer Interaction Control by : Scott C. Asbury
Download or read book Static Performance of a Fixed-Geometry Exhaust Nozzle Incorporating Porous Cavities for Shock-Boundary Layer Interaction Control written by Scott C. Asbury and published by . This book was released on 1999 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Analysis of Passive Shock - Boundary Layer Interaction Control for Improving the Off-design Performance of Jet Exhaust Nozzles by : Craig Allen Hunter
Download or read book An Experimental Analysis of Passive Shock - Boundary Layer Interaction Control for Improving the Off-design Performance of Jet Exhaust Nozzles written by Craig Allen Hunter and published by . This book was released on 1993 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
