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Computer program to determine the irrotational nozzle admittanceIrrotational 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.
Document ID
19730000233
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Bell, W. A. (Georgia Inst. of Tech.)
Zinn, B. T. (Georgia Inst. of Tech.)
Date Acquired
August 7, 2013
Publication Date
November 1, 1973
Subject Category
Mathematics And Information Sciences
Report/Patent Number
LEW-12019
Report Number: LEW-12019
Accession Number
73B10233
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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