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A numerical study of mixing and combustion in hypervelocity flows through a scramjet combustor model
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Krishamurthy, Ramesh |
| Copyright Year | 1993 |
| Description | Interest in high speed, air-breathing propulsion systems such as scramjets has revived in recent years fueled to a large extent by the National Aerospace Plane (NASP) program. These vehicles are expected to fly trans-atmospheric and as a consequence, the Mach number level within the engine/combustor would be rather high (M greater than 5). Ground based testing of such scramjet engines requires a facility that can not only achieve the right Mach number, but also have the proper pressures and temperatures to simulate the combustion processes. At present, only pulse type facilities can provide such high enthalpy flows. The newest of these is the free-piston shock tunnel, T5 located at GALCIT. Recently, a generic combustor model was tested in T5, and the experimental data from that study is analyzed in the present report. The available experimental data from T5 are essentially the static pressures on the injection wall and the one opposite to it. Thus, a principal aim of the present study was to validate the available experimental data by using a proven CFD tool and then investigate the performance characteristics of the combustor model, such as, the mixing efficiency and combustion efficiency. For this purpose, in this study, the code GASP has been used. |
| File Size | 188731 |
| Page Count | 3 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19940023408 |
| Archival Resource Key | ark:/13960/t59d1vm8r |
| Language | English |
| Publisher Date | 1993-12-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Propulsion System Performance Enthalpy Supersonic Combustion Ramjet Engines National Aerospace Plane Program Piston Engines Propulsion System Configurations Combustion Physics Supersonic Combustion Wall Flow Fuel Injection Combustion Chambers Combustion Efficiency Hypervelocity Flow Shock Tunnels Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
