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Cfd Analysis Of Nozzle Jet Plume Effects On Sonic Boom Signature
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Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781794059351 Total Pages :48 pages Book Rating :4.0/5 (593 download)
Book Synopsis Cfd Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature by : National Aeronautics and Space Adm Nasa
Download or read book Cfd Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-14 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational fluid dynamics study is conducted to examine nozzle exhaust jet plume effects on the Sonic boom signature of a supersonic aircraft. A simplified axisymmetric nozzle geometry, representative of the nozzle on the NASA Dryden NF-15B Lift and Nozzle Change Effects on Tail Shock research airplane, is considered. The computational fluid dynamics code is validated using available wind-tunnel sonic boom experimental data. The effects of grid size, spatial order of accuracy. grid type, and flow viscosity on the accuracy of the predicted sonic boom pressure signature are quantified. Grid lines parallel to the Mach wave direction are found to give the best results. Second-order accurate upwind methods are required as a minimum for accurate sonic boom simulations. The highly underexpanded nozzle flow is found to provide significantly more reduction in the tail shock strength in the sonic boom N-wave pressure signature than perfectly expanded and overexpanded nozzle flows. A tail shock train in the sonic boom signature is observed for the highly underexpanded nozzle flow. Axisymmetric computational fluid dynamics simulations show the flow physics inside the F-15 nozzle to be nonisentropic and complex. NASA/TM-2009-214650, AIAA Paper 2009-1054, H-2923, DFRC-938 Bui, Trong T. Armstrong Flight Research Center
Book Synopsis Cfd Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature by : Trong T. Bui
Download or read book Cfd Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature written by Trong T. Bui and published by BiblioGov. This book was released on 2013-07 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational fluid dynamics study is conducted to examine nozzle exhaust jet plume effects on the Sonic boom signature of a supersonic aircraft. A simplified axisymmetric nozzle geometry, representative of the nozzle on the NASA Dryden NF-15B Lift and Nozzle Change Effects on Tail Shock research airplane, is considered. The computational fluid dynamics code is validated using available wind-tunnel sonic boom experimental data. The effects of grid size, spatial order of accuracy. grid type, and flow viscosity on the accuracy of the predicted sonic boom pressure signature are quantified. Grid lines parallel to the Mach wave direction are found to give the best results. Second-order accurate upwind methods are required as a minimum for accurate sonic boom simulations. The highly underexpanded nozzle flow is found to provide significantly more reduction in the tail shock strength in the sonic boom N-wave pressure signature than perfectly expanded and overexpanded nozzle flows. A tail shock train in the sonic boom signature is observed for the highly underexpanded nozzle flow. Axisymmetric computational fluid dynamics simulations show the flow physics inside the F-15 nozzle to be nonisentropic and complex.
Book Synopsis CFD Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature by : Trong T. Bui
Download or read book CFD Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature written by Trong T. Bui and published by . This book was released on 2009 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational fluid dynamics study is conducted to examine nozzle exhaust jet plume effects on the sonic boom signature of a supersonic aircraft. A simplified axisymmetric nozzle geometry, representative of the nozzle on the NASA Dryden NF-15B Lift and Nozzle Change Effects on Tail Shock research airplane, is considered. The computational fluid dynamics code is validated using available wind-tunnel sonic boom experimental data. The effects of grid size, spacial order of accuracy, grid type, and flow viscosity on the accuracy of the predicted sonic boom pressure signature are quantified. Grid lines parallel to the Mach wave direction are found to give the best results. Second-order accurate upwind methods are required as a minimum for accurate sonic boom simulations. The highly underexpanded nozzle flow is found to provide significantly more reduction in the tail shock strength in the sonic boom N-wave pressure signature than perfectly expanded and overexpanded nozzle flows. A tail shock train in the sonic boom signature is observed for the highly underexpanded nozzle flow. Axisymmetric computational fluid dynamics simulations show the flow physics inside the F-15 nozzle to be nonisentropic and complex.
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 Comparison of Jet Plume Shape Predictions and Plume Influence on Sonic Boom Signature by : Raymond L. Barger
Download or read book Comparison of Jet Plume Shape Predictions and Plume Influence on Sonic Boom Signature written by Raymond L. Barger and published by . This book was released on 1992 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 :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 NASA's Contributions to Aeronautics: Aerodynamics, structures, propulsion, controls by :
Download or read book NASA's Contributions to Aeronautics: Aerodynamics, structures, propulsion, controls written by and published by . This book was released on 2010 with total page 980 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.
Book Synopsis NASA's Contributions to Aeronautics by :
Download or read book NASA's Contributions to Aeronautics written by and published by . This book was released on 2010 with total page 980 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 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 Exhaust nozzle plume effects on sonic boom test results for vectored nozzles by : Raymond S. Castner
Download or read book Exhaust nozzle plume effects on sonic boom test results for vectored nozzles written by Raymond S. Castner and published by . This book was released on 2012 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Model Design for the Study of Plume Effects on Sonic Boom for Isolated Exhaust Nozzles by : Raymond S. Castner
Download or read book Wind Tunnel Model Design for the Study of Plume Effects on Sonic Boom for Isolated Exhaust Nozzles written by Raymond S. Castner and published by . This book was released on 2010 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Application of CFD to Sonic Boom Near and Mid Flow-field Prediction by :
Download or read book Application of CFD to Sonic Boom Near and Mid Flow-field Prediction written by and published by . This book was released on 1990 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Combined CFD-DSMC Method for Numerical Simulation of Nozzle Plume Flows by : Jyothish D. George
Download or read book A Combined CFD-DSMC Method for Numerical Simulation of Nozzle Plume Flows written by Jyothish D. George and published by . This book was released on 2000 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Simulation of N-wave and Shaped Supersonic Signature Turbulent Variations by : Trevor Stout
Download or read book Simulation of N-wave and Shaped Supersonic Signature Turbulent Variations written by Trevor Stout and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: One of the design paradigms for the next generation of civil supersonic aircraft targets a reduction in sonic boom amplitude and impulsivity, creating a shaped signature at the ground which is likely more acceptable to the public. The unshaped, conventional N-wave sonic boom is well known to distort due to atmospheric turbulence or wind and temperature fluctuations, randomly increasing or decreasing the loudness perceived by listeners. However, the effect of turbulence on the shaped signature is not well understood. No acoustic databases from powered, fully-shaped aircraft yet exist because these prototypes are currently in development. Thus, the present work uses a numerical model based on an augmented nonlinear KZK propagation equation and simulated shaped signatures to analyze the turbulence effects. The KZK equation accounts for absorption, nonlinearity, advection due to turbulence and resultant diffraction, as well as other propagation effects. A novel implementation of a fully time-domain solution is put forth. As is typically done in the literature, the solution to the KZK equation in two dimensions is predominantly used in the present work, though a computationally-intensive 3D algorithm is applied to a limited case. As part of the recently-completed Sonic Booms in Atmospheric Turbulence (SonicBAT) project, supersonic flyover measurement campaigns were conducted to produce the first database of its kind with acoustic data of N-waves from powered, manned aircraft and concurrent atmospheric turbulence and weather data. One objective was to provide suitable inputs for the present numerical model so that the simulated output statistics could be compared with the measured. This comparison shows reasonable agreement between the model and the measurement for most cases across a wide range of atmospheric and turbulence parameters, suggesting that the KZK model is suitable for predicting full-scale sonic boom loudness variations. Using the validated algorithm, turbulence effects on simulated shaped signatures are analyzed in many hypothetical atmospheres and compared to the effects on the N-wave, revealing that the boom shaping tends to reduce loudness variations. Finally, the prevailing use of 2D simulations in the literature and the present work is qualified by comparison to comparable 3D simulations, finding that inclusion of the third dimension somewhat augments the turbulence effects and increases the predicted probability of high-amplitude N-wave booms.
Book Synopsis Simulation of Nozzle Plume Flows Using a Combined CFD-DSMC Approach by : Jyothish D. George
Download or read book Simulation of Nozzle Plume Flows Using a Combined CFD-DSMC Approach written by Jyothish D. George and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
