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 |
Total Pages | : 48 |
Release | : 2019-01-14 |
Genre | : Science |
ISBN | : 9781794059351 |
Download Cfd Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature Book in PDF, Epub and Kindle
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
Author | : Trong T. Bui |
Publisher | : BiblioGov |
Total Pages | : 50 |
Release | : 2013-07 |
Genre | : |
ISBN | : 9781289230487 |
Download Cfd Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature Book in PDF, Epub and Kindle
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.
Author | : Trong T. Bui |
Publisher | : |
Total Pages | : 40 |
Release | : 2009 |
Genre | : |
ISBN | : |
Download CFD Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature Book in PDF, Epub and Kindle
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.
Author | : Nasa Technical Reports Server (Ntrs) |
Publisher | : BiblioGov |
Total Pages | : 28 |
Release | : 2013-07 |
Genre | : |
ISBN | : 9781289168445 |
Download Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles Book in PDF, Epub and Kindle
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.
Author | : Raymond L. Barger |
Publisher | : |
Total Pages | : 28 |
Release | : 1992 |
Genre | : |
ISBN | : |
Download Comparison of Jet Plume Shape Predictions and Plume Influence on Sonic Boom Signature Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 980 |
Release | : 2010 |
Genre | : Aeronautics |
ISBN | : |
Download NASA's Contributions to Aeronautics: Aerodynamics, structures, propulsion, controls Book in PDF, Epub and Kindle
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.
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 26 |
Release | : 2018-05-22 |
Genre | : |
ISBN | : 9781719392037 |
Download Exhaust Nozzle Plume and Shock Wave Interaction Book in PDF, Epub and Kindle
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
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 26 |
Release | : 2018-06-30 |
Genre | : |
ISBN | : 9781722108878 |
Download Comparison of Jet Plume Shape Predictions and Plume Influence on Sonic Boom Signature Book in PDF, Epub and Kindle
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...
Author | : |
Publisher | : |
Total Pages | : 980 |
Release | : 2010 |
Genre | : Aeronautics |
ISBN | : |
Download NASA's Contributions to Aeronautics Book in PDF, Epub and Kindle
Author | : Song Fu |
Publisher | : Springer Nature |
Total Pages | : 1991 |
Release | : |
Genre | : |
ISBN | : 981974010X |
Download 2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings Book in PDF, Epub and Kindle