Compressor-face boundary condition experiment - Generation of acoustic pulses in annular ducts-Reference-Cited by-同舟云学术

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Compressor-face boundary condition experiment - Generation of acoustic pulses in annular ducts

Published:1996-07-01 Issue: Volume: Page:
ISSN:
Container-title:32nd Joint Propulsion Conference and Exhibit
language:
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Author:

Freund Donald¹,Sajben Miklos¹,Slater John²

Affiliation:

1. Cincinnati, Univ., OH

2. NASA, Lewis Research Center, Cleveland, OH

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1996-2657

Reference10 articles.

1. Turbulence in Supersonic Flow

2. Propagation of sound waves through a blade row

3. Mayer, W.D. and Paynter, G.C."Prediction of Supersonic Inlet Unstart Caused by Freestream Disturbances,"AIAApaper 94-0580.

4. Decher, R., Mayer, D.W.and Paynter,G.C. "On Supersonic Inlet-Engine Stability," AIAA paper 94-3371.

Cited by 9 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Vortex Shedding and Transition Frequencies Associated with Flow Around a Circular Cylinder;AIAA Journal;2003-03

2. Acoustic and Entropy Pulses Created in Duct Flows by Rapid Local Events;AIAA Journal;2003-03

3. Inlet/Compressor System Response to Short-Duration Acoustic Disturbances;Journal of Propulsion and Power;2002-07

4. Acoustic-Wave/Blade-Row Interactions Establish Boundary Conditions for Unsteady Inlet Flows;Journal of Propulsion and Power;2001-09

5. Experiment to Support the Formulation and Validation of Compressor-Face Boundary Conditions;Journal of Propulsion and Power;2000-05

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