Actions for Computer program to determine the irrotational nozzle admittance

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Computer program to determine the irrotational nozzle admittance

Author
Bell, W. A.
Published
Nov 1, 1973.
Physical Description
1 electronic document
Additional Creators
Zinn, B. T.
Online Version

Availability

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
Irrotational nozzle admittance is the boundary condition that must be satisfied by combustor flow oscillations at nozzle entrance. Defined as the ratio of axial velocity perturbation to the pressure perturbation at nozzle entrance, nozzle admittance can also be used to determine whether wave motion in nozzle under consideration adds or removes energy from combustor oscillations.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19730000233.
Accession ID: 73B10233.
LEW-12019.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 16410001