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A study of ingestion and dispersion of engine exhaust products in trailing vortex systems
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Stahara, S. S. Nielsen, J. N. Woolley, J. P. |
| Copyright Year | 1973 |
| Description | Analysis has been made of the ingestion and dispersion of engine exhaust products into the trailing vortex system of supersonic aircraft flying in the stratosphere. The rate of mixing between the supersonic jet and the co-flowing supersonic stream was found to be an order of magnitude less than would be expected on the basis of subsonic eddy-viscosity results. The length of the potential core was 66 nozzle exit radii so that the exhaust gases remain at elevated temperatures and concentrations over much longer distances than previsously estimated. Ingestion started at the end of the potential core and all hot gas from the engine was ingested into the trailing vortex within two core lengths. Comparison between the buoyancy calculations for the supersonic case with nondimensionalized subsonic aircraft contrail data on wake spreading showed good agreement. Velocity and temperature profiles have been specified at various stages of the wake, and the analysis in this report can be used to predict variations of concentrations of species such as nitrogen oxides under conditions of chemical reaction. |
| File Size | 5206591 |
| Page Count | 135 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740008384 |
| Archival Resource Key | ark:/13960/t20c9qn74 |
| Language | English |
| Publisher Date | 1973-11-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Supersonic Flow Jet Mixing Flow Turbulent Wakes Gas Flow Exhaust Gases Vortices Gas Analysis Aircraft Engines Flow Geometry Jet Exhaust Jet Engines Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
