NASA NTRS · 19730000233
Computer program to determine the irrotational nozzle admittance
Abstract
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.
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Bell, W. A., Zinn, B. T.. 1973-11-01. Computer program to determine the irrotational nozzle admittance. https://ntrs.nasa.gov/citations/19730000233
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