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Comparison of the NASA Common Research Model European Transonic Wind Tunnel Test Data to NASA Test Data

Author
Rudnik, Ralf
Published
January 5, 2015.
Physical Description
1 electronic document
Additional Creators
Rivers, Melissa B. and Quest, Jurgen
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
Experimental aerodynamic investigations of the NASA Common Research Model have been conducted in the NASA Langley National Transonic Facility, the NASA Ames 11-ft wind tunnel, and the European Transonic Wind Tunnel. In the NASA Ames 11-ft wind tunnel, data have been obtained at only a chord Reynolds number of 5 million for a wing/body/tail = 0 degree incidence configuration. Data have been obtained at chord Reynolds numbers of 5, 19.8 and 30 million for the same configuration in the National Transonic Facility and in the European Transonic Facility. Force and moment, surface pressure, wing bending and twist, and surface flow visualization data were obtained in all three facilities but only the force and moment, surface pressure and wing bending and twist data are presented herein.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20150006851.
NF1676L-19137.
AIAA SciTech 2015; 5-9 Jan. 2015; Kissimmee, FL; United States.
Terms of Use and Reproduction
Copyright, Distribution as joint owner in the copyright.
View MARC record | catkey: 15414871