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Exp: NASA Rotor 37
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The
NASA Rotor 37 test case, designed and tested originally by Reid and Moore at NASA Lewis (now
NASA Glenn Research Center), is a low aspect ratio inlet stage for an eight-stage core compressor with
a 20:1 pressure ratio.
Primary documentation regarding the experimental data can be found in:
-
Suder, K. L.,
"Experimental Investigation of the Flow Field in a Transonic, an Axial Flow
Compressor With Respect to the Development of Blockage and Loss," NASA TM 107310, October,
1996,
https://ntrs.nasa.gov/citations/19970001675.
-
Suder, K. L. and Celestina, M. L.,
"Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor,"
NASA TM 106711, June, 1995,
https://ntrs.nasa.gov/citations/19950025317.
Other related documentation includes:
- Reid, L. and Moore, R. D.,
"Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor,"
NASA Technical Paper 1337, October 1978,
https://ntrs.nasa.gov/citations/19780025165.
- Reid, L. and Moore, R. D.,
"Performance of Single-Stage Axial-Flow Transonic
Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design
Pressure Ratio of 1.82," NASA Technical Paper 1338, November 1978,
https://ntrs.nasa.gov/citations/19790001889.
- Moore, R. D. and Reid, L.,
"Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05,"
NASA Technical Paper 1659, April, 1980,
https://ntrs.nasa.gov/citations/19800012840.
- Moore, R. D. and Reid, L.,
"Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82,"
NASA Technical Paper 1974, February, 1982,
https://ntrs.nasa.gov/citations/19820011348.
- Denton, J. D.,
"Lessons from Rotor 37,"
Journal of Thermal Science, Vol. 6, No. 1, 1997, pp. 1-13,
https://doi.org/10.1007/s11630-997-0010-9.
The experimental data (along with the geometry, a geometry README file,
and the first two published documents listed above) are provided in the following file. The experimental data in the Excel sheet describes
the performance of the rotor at 100% speed with run conditions and the
profile data at the exit of the test rig.
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Last Updated: 04/20/2023