Performance of Low Pressure Ratio Ejectors for Engine Nacelle Cooling
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Product Code: AIR1191
Revision Number: A
Date Published: 1999-03-01
Issuing Committee:
S-12 Helicopter Powerplant Committee
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.
Product Status: In Stock
File Size:
1407K
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| Current & Historical versions of this standard |
|---|
| Standard |
Date published |
?Status |
| AIR1191A |
1999-03-01 |
Revised |
| AIR1191 |
1971-11-01 |
Reaffirmed |
|
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