Simulation and analysis of aerodynamic external flow field environment for the scramjet-propelled hypersonic vehicle

Abstract

This study addresses the current gap in predicting the aerodynamic environment encountered by scramjet-propelled hypersonic vehicles during flight. Correlation analyses between key simulation parameters and numerical accuracy were conducted based on wind tunnel data. Based on these insights, an optimized aerodynamic environment simulation scheme is proposed. The optimization comprises tailored configurations for different flight regimes, focusing on grid parameters like near-wall y+ values and shock-wave cell aspect ratio for grid strategy, and on the selection of turbulence models and flux schemes for numerical methods. The predicted aero-acoustic, vibrational, and thermal conditions are shown to be extreme, with values reaching 145 dB, 182 g, and 2130 K, respectively. Structural design must prioritize the airfoil’s leading edge, which requires materials with excellent heat resistance to withstand intense aerodynamic heating. Vibration-resistant design should prioritize the airfoil trailing edge. While high-performance materials such as Inconel alloys enhance structural reliability, the predicted peak temperatures exceed their practical service limits; effective thermal management therefore requires integrated solutions combining material selection with active cooling and thermal protection. In environmental testing, the test scope must comprehensively cover the extreme limits of the aforementioned aerodynamic conditions, with thermal tests requiring a peak temperature rise rate of 83 °C s−1 to simulate thermal stresses under extreme flight conditions. Furthermore, as flow velocity increases, the impact of aerodynamic heating on structural vibrations becomes more pronounced, further validating the critical importance of combined thermal-vibration testing.