This content is not included in your SAE MOBILUS subscription, or you are not logged in.
PERFORMANCE OF LOW PRESSURE RATIO EJECTORS FOR ENGINE NACELLE COOLING
- Aerospace Standard
Published May 01, 1989 by SAE International in United States
Downloadable datasets availableAnnotation ability available
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.
|Technical Paper||Computation of Sound Propagation in an Automotive Air Handling System|
Data Sets - Support Documents
|TABLE II||BASIC EQUATIONS|
S-12 Powered Lift Propulsion Committee
* Redlines comparisons are available for those standards listed in the Revision History that contain a radio button. A redline comparison of the current version against a revision is accomplished by selecting the radio button next to the standard and then selecting 'compare'. At this time, Redline versions only exist for some AMS standards. SAE will continue to add redline versioning with ongoing updates to SAE MOBILUS.