Abstract:
1-D tube flow method was adopted for the design of
Φ240mm hypersonic wind tunnel diffuser at Mach Number 6.0, and numerical simulation was carried out in order to select the configuration of the diffuser. Then, experimental test was used to verify the design method of the diffuser. The results show that, in comprehensive consideration of the flow-field performance of the wind tunnel, the resistance pressure ability, and total pressure recover, the diffuser has single stage compression half-cone angle being 15° and second throat diameter being 0.8
De (the exit diameter of the nozzle). The experimental results of the optimal diffuser agree well with corresponding numerical ones. The hypersonic wind tunnel can start smoothly and maintain long-time operation with this diffuser. The optimal diffuser design can be implemented in the construction of new wind tunnel, and the design method of the diffuser provides a reference for the development of similar diffusers in hypersonic wind tunnel.