Actions for Perforations in jet engine supersonic inlet increase shock stability

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Perforations in jet engine supersonic inlet increase shock stability

Author
Keppler, C. R.
Published
Nov 1, 1966.
Physical Description
1 electronic document
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
Modification of a conventional jet engine internal compression supersonic inlet results in increased shock stability and thus, engine instantaneous response to changes in inlet air properties. This technique provides a large amount of bleed near the maximum pressure recovery at the expense of minor bleed flow during critical operation.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19660000528.
Accession ID: 66B10530.
NEO-8.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 16210939