摘要: The decomposition of computational data into dynamic modes is performed on a two-dimensional hypersonic scramjet inlet-isolator to identify the dominant modes of the flow field and identify methods and characteristics of unstart. ... 展开 The decomposition of computational data into dynamic modes is performed on a two-dimensional hypersonic scramjet inlet-isolator to identify the dominant modes of the flow field and identify methods and characteristics of unstart. The analysis is performed on computational fluid dynamic results obtained from VULCAN-CFD simulation without the use of turbulence modeling. The CFD study was compared and validated with prior results utilizing the same geometry to analyze the differences in the inlet-isolator flow physics and ensure proper capturing of the separation region formed by the shock wave boundary layer interaction (SWBLI). This paper outlines the process and results of the dynamic mode decomposition (DMD) analysis of the computational time-resolved snapshots of the pressure data into dynamic modes. The results show the spectral content and dominant mode structures captured from unsteady behavior of two primary flow cases. These simulated normal outflow conditions at the isolator exit as well as imposing a blockage in order to generate unstart and visualize the dominant modes generated by imposing these unfavorable operating conditions. 收起