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Please see the full NASA Common Research Model website for current information.
NTF Test Data
A test of the new NASA Common Research Model with a Natural Laminar Flow (CRM-NLF) semispan wing in the NASA Langley National Transonic Facility (NTF) was completed in October 2018. The main focus of this test was the evaluation of the extent of laminar flow on the CRM-NLF wing at various Reynolds numbers and test conditions. During this test, data were acquired at chord Reynolds numbers from 10 to 30 million and at Mach numbers ranging from 0.84 to 0.86. This investigation provided valuable insight into the necessary procedures for laminar flow testing in the NTF. It also significantly advanced the new carbon based heating layer technique to improve the quality of transition visualization data from temperature sensitive paint (TSP) in a cryogenic wind tunnel.
Related Files and Data
General information on the wind tunnel data can be downloaded by clicking here.
The force and moment data from the NTF test can be downloaded by clicking here.
Files in jpg format of the post-processed Temperature Sensitive Paint images from 4 data points obtained in the NTF test can be downloaded below:
 p2585 |  p2550 |  p2537 |
 p2448 |  p2436 |  p2523 |
 p2525 |  p2526 |  p2524 |