JAMP  Vol.2 No.6 , May 2014
Aerodynamic Optimization of the Expansion Section in a Hypersonic Quiet Nozzle Based on Favorable Pressure Effect
Abstract: Maximum expansion angle is the primary parameter for the design of expansion section of hypersonic quiet nozzle. According to the quantity of maximum expansion angle, expansion section could be classified as fast expansion and slow expansion. In order to diminish the effect of instability of Görtler vortex, gradually, slow expansion was employed for quiet nozzle design. Based on the favorable pressure effect, the maximum expansion angle is optimized in this paper, and a considerable selective session of maximum expansion angle is obtained. The trend that slow expansion is employed instead of fast expansion is explained, and a new method is established for aerodynamic optimization of expansion section contour in a quiet nozzle.
Cite this paper: Gong, J. , Yao, D. and Liu, X. (2014) Aerodynamic Optimization of the Expansion Section in a Hypersonic Quiet Nozzle Based on Favorable Pressure Effect. Journal of Applied Mathematics and Physics, 2, 443-448. doi: 10.4236/jamp.2014.26054.

[1]   Beckwith, I.E. (1975) Development of a High Reynolds Number Quiet Tunnel for Transition Research. AIAA Journal, 13, 300-306.

[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.

[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.