Subjects: Mechanics >> Basic Mechanics submitted time 2023-04-24 Cooperative journals: 《应用力学学报》
Abstract： The Mach 4.5 test in a conventional tran-supersonic wind tunnel is often accompanied by the phenomenon of air liquefaction,resulting in low reliability of the test data.The Mach 4.5 nozzle developed in a hypersonic wind tunnel has the ability to heat the airflow,which can provide more accurate test data.At present,the test capability of Mach 4.5 is not available in China for the 0.5-meter hypersonic wind tunnel.The axisymmetric nozzle profile was calculated by the inviscid flow calculation method,and the boundary layer was modified by the Sivells-Payne method.Then,numerical simulation was carried out.It was proved that the calculated profile met the GJB design requirements of Mach number and can be put into production.
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