The Study of Design and Installation Process for Supersonic Nozzle

Abstract:

A practical optimal design method of supersonic nozzle is proposed for a supersonic wind tunnel’s design. Design a set of nozzle wall lines with the same nozzle length and different Mach numbers 1.5, 2.0, 2.5. Use numerical simulation method for the verify and analysis of the designed nozzle. Mainly study the impact of the installation gradient between nozzle and test section on flow field quality. This wind tunnel is the subsonic, transonic and supersonic wind tunnel and its test section cross is 0.2 m × 0.2 m .The impact on flow field quality of the test section was studied quantitatively by using the numerical simulation method. The installation gradient index was given. It has some practical value to the construction of supersonic wind tunnel. At present, this study has been applied in construction of the wind tunnel. The gradient of the test section import shall not be greater than 0.5 mm.

• Periodical: Advanced Materials Research (Volume 569)
• Pages: 500-503
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.569.500
• Online since: September 2012
• Authors: Lian Sheng Wu, Guang Li Li, Qi Fu
• Keywords: Flow Field Quality, Installation Gradient, Numerical Simulation, Supersonic Nozzle, Wind Tunnel’s Design

References

[1] Ronglin Wu, Zhenyu Wang．Design principle wind tunnel[M]．Beijing: Beijing Institute of Aeronautics Press．(1985).

[2] Zhengchong Liu. Aerodynamic and structural design high and low speed wind tunnel [M]. Beijing: National Defence Industry Press. (2003).

[3] Shining Liu．Design and experimental study of the binary supersonic nozzle[J] ．Nanjing: Nanjing Aeronautical Institute of Technology.

[4] Frederick L. Shope, Contour Design Techniques for Super/Hypersonic Wind Tunnel Nozzles, AIAA 2006-3665.

DOI: 10.2514/6.2006-3665