The study of design and installation process for Supersonic nozzle
A practical optimal design method of supersonic nozzle is proposed for a supersonic wind tunnels 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.
supersonic nozzle wind tunnels design installation gradient numerical simulation flow field quality
Liansheng Wu Guangli Li Qi Fu
Flued Engineering Research Institute, Shenyang Aerospace University Shenyang, China Testing Technology Laboratory of Jet Propulsion System, Shenyang Aerospace University, Shenyang, Chi
国际会议
厦门
英文
500-503
2012-06-05（万方平台首次上网日期，不代表论文的发表时间）