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SAE AIR 1191A:1999-03-01
Performance of Low Pressure Ratio Ejectors for Engine Nacelle CoolingMore info
A general method for the preliminary design of a single, straight-sided, low subsonic ejector is presented. The method is based on the information presented in References 1, 2, 3, and 4, and utilizes analytical and empirical data for the sizing of the ejector mixing duct diameter and flow length. The low subsonic restriction applies because compressibility effects were not included in the development of the basic design equations. The equations are restricted to applications where Mach numbers within the ejector primary or secondary flow paths are equal to or less than 0.3.
| Author | SAE |
|---|---|
| Editor | SAE |
| Document type | Standard |
| Format | File |
| ICS | 49.050 : Aerospace engines and propulsion systems |
| Number of pages | 47 |
| Replace | SAE AIR 1191:1989-05-01 |
| Set | AEROPAKS10U-10 |
| Year | 1990 |
| Document history | SAE AIR 1191:1989-05-01 |
| Country | USA |
| Keyword | SAE 1191;SAE AIR1191A;SAE AIR1191A;SAE AIR 1191 |