Large Eddy Simulation of Transonic Flow Field in NASA Rotor 37-Reference-Cited by-同舟云学术

Large Eddy Simulation of Transonic Flow Field in NASA Rotor 37

Published:2009-01-05 Issue: Volume: Page:
ISSN:
Container-title:47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition
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Author:

Hah Chunill¹

Affiliation:

1. NASA/Glenn

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2009-1061

Reference19 articles.

1. Reid, L. and Moore, R. D. “Design and Overall Performance of Four Highly-Loaded, High Speed Inlet Stages for an Advanced, HighPressureRatioCoreCompressor,”NASA TP-1337, 1978.

2. Reid, L. and Moore, R. D. “Performance of a Single-Stage Axial-Flow Transonic Compressor with Rotor and Stator Aspect Ratios of1.19 and1.26, Respectively, and with Design PressureRatioof1.82, NASA TP-1338, 1978.

3. Experimental Study of Low Aspect Ratio Compressor Blading

4. Suder, K. L., and Celestina, M. L. “Experimental and Computational Investigation of the Tip Clearance Flow in a TransonicAxial CompressorRotor,”NASA TM-106711, 1994.

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