The influence of a local change in surface temperature of a contoured nozzle corresponding to the Mach number M = 6 on the boundary layer stability and laminar-turbulent transition is numerically studied. The profiles of the laminar boundary layer are obtained by solving the Navier-Stokes equations with the use of the Ansys Fluid software system. N-factors of the growth rates of the Goertler vortices and also disturbances of the first and second Mack modes are calculated in the approximation of the linear stability theory. It is demonstrated that local heating ensures lower growth rates of the amplitudes of the Goertler vortices and the first Mack mode as compared to the base case; the more intense the heating, the more expressed this effect. The growth rate of the amplitude of the second-mode disturbances decreases during local heating of the nozzle to a temperature close to the stagnation temperature and increases at higher temperatures of local heating. It is found that local cooling leads to an increase in the growth rates of the amplitudes of the Goertler vortices and second Mack mode. The amplitude of the first Mack mode in the cooling region is smaller than that in the base case; however, further downstream, it is much greater than that in the base case. It is found that the surface of contoured nozzles should be heated in the region of the maximum growth rates of the amplitudes of the Goertler vortices; the higher the temperature, the more pronounced the expected effect. However, the maximum possible temperature is determined by the growth of the second Mack mode. The optimal option is to use the temperature of local heating of the surface at which the growth rate of the amplitude of the second mode is smaller than that of the Goertler vortices.

数值研究了对应于马赫数M = 6的异型喷嘴表面温度的局部变化对边界层稳定性和层流湍流转变的影响。层边界层的轮廓是通过使用Ansys Fluid软件系统求解Navier-Stokes方程获得的。线性稳定性理论的近似值可计算出Goertler涡旋增长率的N因子，以及第一和第二个Mack模态的扰动。事实证明，与基本情况相比，局部加热确保了Goertler涡旋和第一个Mack模式振幅的增长率较低；加热越剧烈，这种效果越明显。在喷嘴的局部加热到接近停滞温度的温度期间，第二模式扰动的幅度的增长速率减小，而在局部加热的较高温度下，第二模式扰动的幅度的增长率增大。发现局部冷却导致Goertler涡旋和第二Mack模式的振幅的增长率增加。冷却区域中第一麦克模式的振幅小于基本情况下的振幅。但是，在更下游，它比基本情况下的要大得多。发现轮廓喷嘴的表面应在Goertler涡旋振幅的最大增长率的区域内加热；温度越高，预期效果越明显。但是，最大可能温度取决于第二麦克模式的增长。