Cfd Analysis Of Nozzle Jet Plume Effects On Sonic Boom Signature
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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
language : en
Publisher: Independently Published
Release Date : 2019-01-14
Cfd Analysis Of Nozzle Jet Plume Effects On Sonic Boom Signature written by National Aeronautics and Space Adm Nasa and has been published by Independently Published this book supported file pdf, txt, epub, kindle and other format this book has been release on 2019-01-14 with Science categories.
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
Comparison Of Jet Plume Shape Predictions And Plume Influence On Sonic Boom Signature
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Author : Raymond L. Barger
language : en
Publisher:
Release Date : 1992
Comparison Of Jet Plume Shape Predictions And Plume Influence On Sonic Boom Signature written by Raymond L. Barger and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1992 with Jets categories.
2023 Asia Pacific International Symposium On Aerospace Technology Apisat 2023 Proceedings
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Author : Song Fu
language : en
Publisher: Springer Nature
Release Date :
2023 Asia Pacific International Symposium On Aerospace Technology Apisat 2023 Proceedings written by Song Fu and has been published by Springer Nature this book supported file pdf, txt, epub, kindle and other format this book has been release on with categories.
Exhaust Nozzle Plume And Shock Wave Interaction
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-05-22
Exhaust Nozzle Plume And Shock Wave Interaction written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-05-22 with categories.
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
Nasa S Contributions To Aeronautics
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Author :
language : en
Publisher:
Release Date : 2010
Nasa S Contributions To Aeronautics written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2010 with Aeronautics categories.
Nasa S Contributions To Aeronautics Aerodynamics Structures Propulsion Controls
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Author :
language : en
Publisher:
Release Date : 2010
Nasa S Contributions To Aeronautics Aerodynamics Structures Propulsion Controls written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2010 with Aeronautics categories.
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.
Comparison Of Jet Plume Shape Predictions And Plume Influence On Sonic Boom Signature
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-06-30
Comparison Of Jet Plume Shape Predictions And Plume Influence On Sonic Boom Signature written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-06-30 with categories.
An Euler shock-fitting marching code yields good agreement with semiempirically determined plume shapes, although the agreement decreases somewhat with increasing nozzle angle and the attendant increase in the nonisentropic nature of the flow. Some calculations for the low boom configuration with a simple engine indicated that, for flight at altitudes above 60,000 feet, the plume effect is dominant. This negates the advantages of a low boom design. At lower altitudes, plume effects are significant, but of the order that can be incorporated into the low boom design process. Barger, Raymond L. and Melson, N. Duane Langley Research Center RTOP 505-59-53-01...
Exhaust Nozzle Plume Effects On Sonic Boom Test Results For Vectored Nozzles
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Author : Raymond S. Castner
language : en
Publisher:
Release Date : 2012
Exhaust Nozzle Plume Effects On Sonic Boom Test Results For Vectored Nozzles written by Raymond S. Castner and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2012 with categories.
Wind Tunnel Model Design For The Study Of Plume Effects On Sonic Boom For Isolated Exhaust Nozzles
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Author : Raymond S. Castner
language : en
Publisher:
Release Date : 2010
Wind Tunnel Model Design For The Study Of Plume Effects On Sonic Boom For Isolated Exhaust Nozzles written by Raymond S. Castner and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2010 with categories.
Cfd Study Of Turbo Ramjet Interactions In Hypersonic Airbreathing Propulsion System
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-06
Cfd Study Of Turbo Ramjet Interactions In Hypersonic Airbreathing Propulsion System written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-06 with categories.
Advanced airbreathing propulsion systems used in Mach 4-6 mission scenarios, usually involve turbo-ramjet configurations. As the engines transition from turbojet to ramjet, there is an operational envelope where both engines operate simultaneously. In the first phase of our study, an over/under nozzle configuration was analyzed. The two plumes from the turbojet and ramjet interact at the end of a common 2-D cowl, where they both reach an approximate Mach 3.0 condition and then jointly expand to Mach 3.6 at the common nozzle exit plane. For the problem analyzed, the turbojet engine operates at a higher nozzle pressure ratio than the ramjet, causes the turbojet plume overpowers the ramjet plume, deflecting it approximately 12 degrees downward and in turn the turbojet plume is deflected 6 degrees upward. In the process, shocks were formed at the deflections and a shear layer formed at the confluence of the two jets. This particular case was experimentally tested and the data were used to compare with a computational fluid dynamics (CFD) study using the PARC2D code. The CFD results were in good agreement with both static pressure distributions on the cowl separator and on nozzle walls. The thrust coefficients were also in reasonable agreement. In addition, inviscid relationships were developed around the confluence point, where the two exhaust jets meet, and these results compared favorably with the CFD results. In the second phase of our study, a 3-D CFD solution was generated to compare with the 2-D solution. The major difference between the 2-D and 3-D solutions was the interaction of the shock waves, generated by the plume interactions, on the sidewall. When a shock wave interacts with a sidewall and sidewall boundary layer, it is called a glancing shock sidewall interaction. These interactions entrain boundary layer flow down the shockline into a vortical flow pattern. The 3-D plots show the streamlines being entrained down the shockline. The pressure of the flow a...