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PERFORMANCE OF LOW PRESSURE RATIO EJECTORS FOR ENGINE NACELLE COOLING
- Aerospace Standard
- AIR1191
- Issued
Downloadable datasets available
Annotation ability available
Sector:
Issuing Committee:
Language:
English
Scope
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.
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Topic
Data Sets - Support Documents
| Title | Description | Download |
|---|---|---|
| TABLE I | NOMENCLATURE | |
| TABLE II | BASIC EQUATIONS |
Issuing Committee
S-12 Powered Lift Propulsion Committee
Provides guidance and standardization for the better utilization of helicopter powerplants through studies of current practices in engine design, engine/airframe interface, and engine operation.
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