[1] Beckwith, I.E. (1975) Development of a High Reynolds Number Quiet Tunnel for Transition Research. AIAA Journal, 13, 300-306. http://dx.doi.org/10.2514/3.49695
[2] Anders, J.B., Stainback, P.C. and Beckwith, I.E. (1978) A New Technique for Reducing Test Section Noise in Supersonic Wind Tunnels. AIAA Paper: 1978-0817.
[3] Beckwith, I.E. and Moore, W.O. (1982) Mean Flow and Noise Measurements in a Mach 3.5 Pilot Quiet Tunnel. AIAA Paper: 1982-0569.
[4] Chen, F.J., Wilkinson, S.P. and Beckwith, I.E. (1991) Görtler Instability and Hypersonic Quiet Nozzle Design. AIAA Paper: 1991-1648.
[5] Schneider, S.P. (1998) Design and Fabrication of a 9.5-inch Mach-6 Quiet-Flow Ludwieg Tube. AIAA Paper: 1998-2511.
[6] Zhou, Y.W., Chang, X.Y., Yi, S.H. and Zhang, Y. (2002) The Aerodynamic Design of Supersonic Quiet Wind Tunnel. Experiments and Measurements in Fluid Mechanics, 16, 61-66.
[7] Schneider, S.P. (2008) Development of Hypersonic Quiet Tunnels. Journal of Spacecraft and Rockets, 45, 641-664. http://dx.doi.org/10.2514/1.34489
[8] Zhou, Y.W. and Yi, S.H. (2010) Summarization of the Characteristics and De-velopment of Hypersonic Quiet Wind Tunnel. Journal of Experimental Mechanics, 25, 167-172.
[9] Beckwith, I.E. and Holley, B.B. (1981) Görtler Vortices and Transition in Wall Boundary Layers of Two Mach-5 Nozzles. NASA-TP-1869.
[10] Schneider, S.P. (1998) Design of a Mach-6 Quiet-Flow Wind-Tunnel Nozzle Using the eN Me-thod for Transition Estimation. AIAA Paper: 1998-0547.