The influence due to the shape of the expanding part of supersonic nozzles on the gas-dynamic structures formed in the ducts of high-altitude rocket and aerodynamic test benches has been studied. The research was carried out using the means of computational gas dynamics with the example of a model gas-dynamics tube with three replaceable supersonic nozzles having identical throat and outlet-section diameters. For confirming the adequacy of the models and methods used, the calculated values were compared to experimental ones. To this end, a model setup was developed, manufactured, and tested. Air with ambient temperature was used as the working medium. Another goal of the study was to compare the calculations performed with the use of different turbulence models.

研究了超音速喷管膨胀部分的形状对高空火箭和气动试验台管道内形成的气动力结构的影响。该研究是使用计算气体动力学的方法以模型气体动力学管为例进行的，该管具有三个具有相同喉部和出口截面直径的可更换超音速喷嘴。为了确认所使用的模型和方法的充分性，将计算值与实验值进行了比较。为此，开发、制造和测试了模型设置。使用环境温度的空气作为工作介质。该研究的另一个目标是比较使用不同湍流模型进行的计算。