Effects of aeroelasticity on performance of hypersonic inlet

In order to study the effects of the aeroelasticity on the performance of the hypersonic inlet, based on the mode method, aeroelasticity analysis of the two-dimensional thin panel structure inlet with different thickness is conducted. First, the two-dimensional inlet GK01 experimental model of DLR is numerically simulated, and the calculation results are in good agreement with the experimental results, which validates the reliability of the calculation method. Based on this model, in the time domain, aeroelasticity of the two-dimensional inlet thin panel structure with different thickness is analyzed. The two-dimensional mode is extracted from three-dimensional mode. The calculation results show that: (1)with increase of the panel structure's thickness, the aeroelasticity properties of inlet change from divergence to convergence. And the natural frequency of the structure is close, the general displacement shows the "beat" phenomenon over time. (2)The performance of the inlet will be affected significantly even with a small amplitude vibration. In this study, the maximum variation amplitude of flow coefficient, total pressure recovery coefficient and pressure rise ratio reached to 14.34%, 25.07% and 110.37%, respectively. Therefore, the effects of the aeroelasticity of the inlet structure should be taken into consideration while designing the structure.