Flight Simulation Characteristics of the Langley High Reynolds Number Cryogenic Transonic Tunnel
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Va.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.60395
Reference4 articles.
1. High-Reynolds-Number Cryogenic Wind Tunnel
Cited by 6 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. A Study of Potential Test Capabilities of the NASA Langley 0.3-Meter Transonic Cryogenic Wind Tunnel;30th AIAA Aerodynamic Measurement Technology and Ground Testing Conference;2014-06-13
2. A study on high subsonic airfoil flows in relatively high Reynolds number by using OpenFOAM;Journal of Thermal Science;2014-03-11
3. Preliminary assessment of tunnel wall interference in the NDA cryogenic wind tunnel;Journal of Aircraft;1994-09
4. Preliminary assessment of tunnel wall interference in the NDA cryogenic wind tunnel;31st Aerospace Sciences Meeting;1993-01-11
5. Reynolds Number Effects on Boattaildrag of Wing-Bodies;Journal of Aircraft;1977-05
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