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Status of flow separation prediction in liquid propellant rocket nozzles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Schmucker, R. H. |
| Copyright Year | 1974 |
| Description | Flow separation which plays an important role in the design of a rocket engine nozzle is discussed. For a given ambient pressure, the condition of no flow separation limits the area ratio and, therefore, the vacuum performance. Avoidance of performance loss due to area ratio limitation requires a correct prediction of the flow separation conditions. To provide a better understanding of the flow separation process, the principal behavior of flow separation in a supersonic overexpanded rocket nozzle is described. The hot firing separation tests from various sources are summarized, and the applicability and accuracy of the measurements are described. A comparison of the different data points allows an evaluation of the parameters that affect flow separation. The pertinent flow separation predicting methods, which are divided into theoretical and empirical correlations, are summarized and the numerical results are compared with the experimental points. |
| File Size | 2434294 |
| Page Count | 69 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750003989 |
| Archival Resource Key | ark:/13960/t8jd9n74f |
| Language | English |
| Publisher Date | 1974-11-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Boundary Layer Separation Nozzle Design Wall Pressure Nozzle Flow Supersonic Nozzles Flow Distribution Pressure Distribution Liquid Propellant Rocket 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 |
