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Cfd analyses of combustor and nozzle flowfields
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Tsuei, Hsin-Hua Merkle, Charles L. |
| Copyright Year | 1993 |
| Description | The objectives of the research are to improve design capabilities for low thrust rocket engines through understanding of the detailed mixing and combustion processes. A Computational Fluid Dynamic (CFD) technique is employed to model the flowfields within the combustor, nozzle, and near plume field. The computational modeling of the rocket engine flowfields requires the application of the complete Navier-Stokes equations, coupled with species diffusion equations. Of particular interest is a small gaseous hydrogen-oxygen thruster which is considered as a coordinated part of an ongoing experimental program at NASA LeRC. The numerical procedure is performed on both time-marching and time-accurate algorithms, using an LU approximate factorization in time, flux split upwinding differencing in space. The integrity of fuel film cooling along the wall, its effectiveness in the mixing with the core flow including unsteady large scale effects, the resultant impact on performance and the assessment of the near plume flow expansion to finite pressure altitude chamber are addressed. |
| File Size | 304641 |
| Page Count | 5 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19940018560 |
| Archival Resource Key | ark:/13960/t7tn24q11 |
| Language | English |
| Publisher Date | 1993-11-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Navier-stokes Equation Core Flow Combustion Physics Computational Fluid Dynamics Flow Distribution Rocket Exhaust Hydrogen Oxygen Engines Film Cooling Combustion Chambers Propellant Combustion 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 |
