Influence of thermal nonequilibrium on the laminar–turbulent transition is studied on the basis of the e^N -method for two widespread flow regimes of a supersonic boundary layer at Mach number M = 4.5. The set of actual frequencies of spatial disturbances was determined from the neutral stability curves for temporal disturbances. The families of N-factor curves were calculated for selected frequencies. The transition Reynolds number was determined for a given transition factor N_T = 8 from the envelopes of the families of N-factor curves. Calculations show that for the level of the vibrational excitation below the dissociation limit and for N_T = 8 the transition zone shifts downstream by 1214 % compared to a perfect gas.

在马赫数 M = 4.5 的超音速边界层的两种广泛流动状态下，基于e ^N 方法研究了热非平衡对层流-湍流转变的影响。空间扰动的实际频率集是从时间扰动的中性稳定性曲线确定的。计算选定频率的N因子曲线族。从N因子曲线族的包络线确定给定过渡因子N _T = 8的过渡雷诺数。计算表明，对于低于解离极限的振动激发水平和对于N _T = 8 与完美气体相比，过渡区向下游移动了 1214 %。