Flow Visualization Measurement Techniques for High-Speed Transition Research in the Boeing/AFOSR Mach-6 Quiet Tunnel
Author:
Affiliation:
1. Purdue University
2. NASA Langley Research Center
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2003-4583
Reference74 articles.
1. Pate, S. R. Effects of Wind Tunnel Disturbances on Boundary-Layer Transition with Emphasis on Radiated Noise: A Review. Paper 80-0431, AIAA, March1980.
2. Schneider, S. P. Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition. Journal of Spacecraft and Rockets, 38(3):323-333, May-June2001.
3. Chen, F.J., Malik, M. R., and Beckwith, I. E. Boundary-Layer Transition on a Cone and Flat Plate at Mach 3.5. AIAA Journal, 27(6):687-693, June1989.
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