Abstract This paper introduces the design performance parameters, flow field calibration results and standard model force measurements of Φ120 hypersonic wind tunnel of Zhejiang University. This wind tunnel adopts conventional "blow-suck" layout. The diameter of the nozzle outlet is 120 mm; the design operation Mach number is 5.0, 6.0 and 7.0; the total pressure of the incoming flow is 0.2~2.0 MPa; the total temperature of the incoming flow is 400~700 K; and the running time is not less than 10 seconds. The flow field calibration results show that the uniform region diameters of the 5.0/6.0/7.0 nozzles are more than 90mm; the average Mach numbers of the uniform region are 5.07, 6.05 and 6.94; the rms deviations are 0.018, 0.015 and 0.023; and the axial Mach gradients of the uniform region are 0.021, 0.016 and 0.031 respectively. All the above key parameters reach the GJB1179A-2012 qualified indices, and some parameters reach the GJB1179A-2012 advanced indices. The aerodynamic force measurement results of the AGARD HB-2 standard model in the Φ120 hypersonic wind tunnel are consistent with the simulation results of in-house code GRAND and the reference experimental results in GJB4399-2002. In summary, Φ120 hypersonic wind tunnel has a wide range of parameters, which is applicable for hypersonic aerodynamic teaching experiments and advanced scientific research subjects such as hypersonic complex flow mechanism and flow control for heat and drag reduction.
2022, Vol. 5 
