Numerical Investigation of Shock-Reflection Phenomena in Overexpanded Supersonic Jets
Numerical Investigation of Shock-Reflection Phenomena in Overexpanded Supersonic Jets
复制标题
超膨胀超音速喷气机激波反射现象的数值研究
作者：
A. Hadjadj;A. Kudryavtsev;M. Ivanov
对超声速平面射流在过膨胀条件下由规则反射向马赫反射的过渡进行了数值研究。首先，通过求解欧拉方程进行无粘计算。结果表明，随着射流/环境压力比的减小和增大，存在滞回现象，导致喷嘴-唇激波的入射角发生变化，从而导致从规则激波到马赫反射激波再回到规则激波。前向和后向跃迁的角度分别接近理论脱离和冯·诺依曼准则。此外，湍流计算（通过使用改进的双方程模型）进行了研究在更现实的情况下的转变
The transition from regular to Mach reflection in a supersonic planar jet operating under overexpanded conditions has been studied numerically. First, inviscid computations are performed by the solution of Euler equations. The results demonstrate that a hysteresis phenomenon is observed as the jet/ambient pressure ratio decreases and increases, causing a change in the angle of incidence of the nozzle-lip shock and, as a consequence, the transition from regular to Mach reflection and back. The angles of forward and backward transitions are close to the theoretical detachment and von Neumann criteria, respectively. Furthermore, turbulent computations (by the use of an improved two-equation model) are conducted to investigate the transition in a more realistic situation