Stability of the laminar boundary layer on the surface of a hypersonic nozzle for the Mach number M = 6 of the Transit-M wind tunnel is calculated. The laminar boundary-layer profiles are obtained by solving the Navier-Stokes equations numerically within the framework of the Ansys Fluent software. N-factors of the Goertler vortices and of the first and second Mack modes are obtained in the approximation of the linear stability theory. It is demonstrated that the Goertler vortices are the most unstable disturbances for the nozzle under consideration. Empirical dependences of the local Reynolds number of the laminar-turbulent transition on the N-factor and unit Reynolds number are determined.

中文翻译：

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Mach 6轮廓喷嘴的层流边界层稳定性计算

计算了Transit-M风洞的马赫数M = 6时高超声速喷嘴表面上的层状边界层的稳定性。层流边界层轮廓是通过在Ansys Fluent软件的框架内通过数值求解Navier-Stokes方程获得的。线性稳定性理论的近似值获得了Goertler涡旋以及第一和第二个Mack模式的N因子。结果表明，对于所考虑的喷嘴，Goertler涡旋是最不稳定的扰动。确定层流湍流转变的局部雷诺数对N因子和单位雷诺数的经验依赖性。