In the present study, the shock-disturbances interaction in hypersonic inviscid flows with real gas effects is studied by applying a high-order accurate numerical method with the shock capturing technique. To consider real gas effects, the equilibrium air model is utilized here. The strong conservative form of the unsteady compressible Euler equations in the 2D generalized curvilinear coordinates is formulated and the resulting system of equations for the equilibrium air model is discretized by using the fifth-order finite-difference WENO scheme in space and the explicit third-order TVD Runge–Kutta scheme in time to provide a highly accurate and robust equilibrium airflow solver. The solution methodology adopted based on the high-order WENO scheme with the shock capturing technique can reasonably simulate the strong discontinuities in the solution domain without needing any numerical artifact and this feature makes the solution method suitable for the shock-disturbances interaction in hypersonic flows in which real gas effects are to be considered. To study the physical phenomenon of the shock-disturbances interaction problem in high-speed inviscid equilibrium airflows, two test cases are simulated by applying the solution methodology adopted. In the first test case, the interaction between the incoming fast acoustic wave with the bow shock formed around a cylinder with the nose radius of $R_N=0.0381$ m at $M_{\infty }=8.03$ and $T_{\infty }=182.333$ K is simulated. In the second test case, the cylinder radius is taken $R_N=2.54\times 10^{-2}$ m and the upstream velocity and temperature are $u_{\infty }=5590\mathrm{m/s}$ and $T_{\infty }=1833$ K, respectively, and all kinds of free stream disturbances, including the entropy wave and the fast and slow acoustic waves, for different wave numbers are considered. The computations are carried out for both the perfect gas and equilibrium air models and the effects of real gas on both the mean and disturbances fields are also studied. The present study introduces the first-known numerical investigation of the shock-disturbances interaction in hypersonic flow over blunt noses with real gas effects in which the numerical results obtained are thoroughly validated by the analytical/theoretical ones and good agreement is found.

在本研究中，通过应用具有激波捕获技术的高阶精确数值方法，研究了具有真实气体效应的高超声速无粘性流中激波-扰动相互作用。为了考虑真实的气体效应，这里使用了平衡空气模型。建立了二维广义曲线坐标中非定常可压缩欧拉方程的强保守形式，并通过使用空间中的五阶有限差分 WENO 格式和显式三阶来离散平衡空气​​模型的方程组TVD Runge-Kutta 方案及时提供高度准确和稳健的平衡气流求解器。采用基于高阶 WENO 方案和激波捕获技术的求解方法可以合理模拟求解域中的强不连续性，无需任何数值伪影，这一特点使得该求解方法适用于高超声速流动中的激扰相互作用。需要考虑哪些真实的气体效应。为了研究高速无粘平衡气流中冲击-扰动相互作用问题的物理现象，应用所采用的求解方法模拟了两个测试案例。在第一个测试案例中，传入的快声波与弓形激波之间的相互作用在一个圆柱体周围形成，该圆柱体的机头半径为 为了研究高速无粘性平衡气流中冲击-扰动相互作用问题的物理现象，应用所采用的求解方法模拟了两个测试案例。在第一个测试案例中，传入的快声波与弓形激波之间的相互作用在一个圆柱体周围形成，该圆柱体的机头半径为 为了研究高速无粘平衡气流中冲击-扰动相互作用问题的物理现象，应用所采用的求解方法模拟了两个测试案例。在第一个测试案例中，传入的快声波与弓形激波之间的相互作用在一个圆柱体周围形成，该圆柱体的机头半径为${\mathrm{电阻}}_N=0.0381$ 米 ${米}_{\infty }=8.03$ 和 ${吨}_{\infty }=182.333$K 是模拟的。在第二个测试用例中，采用圆柱半径${\mathrm{电阻}}_N=2.54\times 10^{-2}$ m 和上游速度和温度是 ${你}_{\infty }=5590\mathrm{多发性硬化症}$ 和 ${吨}_{\infty }=1833$K，分别考虑不同波数下的各种自由流扰动，包括熵波和快慢声波。对完美气体模型和平衡空气模型都进行了计算，并且还研究了真实气体对平均场和扰动场的影响。本研究介绍了第一个已知的对钝头上高超声速流中具有真实气体效应的冲击-扰动相互作用的数值研究，其中获得的数值结果通过分析/理论结果得到了彻底验证，并且发现了良好的一致性。