Computational and Experimental Characterization of the Mach 6 Facility Nozzle Flow for the Enhanced Injection and Mixing Project at NASA Langley Research Center
| Autor: | Karen F. Cabell, Bradley J. Passe, Tomasz G. Drozda, Robert A. Baurle |
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| Rok vydání: | 2017 |
| Předmět: |
020301 aerospace & aeronautics
Engineering business.industry Nozzle Pitot tube 02 engineering and technology Static pressure 01 natural sciences 010305 fluids & plasmas law.invention Physics::Fluid Dynamics symbols.namesake 0203 mechanical engineering Mach number law 0103 physical sciences Combustor symbols Total air temperature Scramjet Aerospace engineering business Ramjet |
| Zdroj: | 55th AIAA Aerospace Sciences Meeting. |
| Popis: | Computational fluid dynamics analyses and experimental data are presented for the Mach 6 facility nozzle used in the Arc-Heated Scramjet Test Facility for the Enhanced Injection and Mixing Project (EIMP). This project, conducted at the NASA Langley Research Center, aims to investigate supersonic combustion ramjet (scramjet) fuel injection and mixing physics relevant to flight Mach numbers greater than 8. The EIMP experiments use a two-dimensional Mach 6 facility nozzle to provide the high-speed air simulating the combustor entrance flow of a scramjet engine. Of interest are the physical extent and the thermodynamic properties of the core flow at the nozzle exit plane. The detailed characterization of this flow is obtained from three-dimensional, viscous, Reynolds-averaged simulations. Thermodynamic nonequilibrium effects are also investigated. The simulations are compared with the available experimental data, which includes wall static pressures as well as in-stream static pressure, pitot pressure and total temperature obtained via in-stream probes positioned just downstream of the nozzle exit plane. |
| Databáze: | OpenAIRE |
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