Abstract: Simulations and experiments were conducted to investigate the fatigue failure of composite materials in hypersonic vehicles subjected to high-intensity acoustic loading. A C/SiC thin-walled structure was investigated, and, accounting for the spatial correlation characteristics of the traveling-wave acoustic field, the modal stress recovery method was utilized to obtain the RMS stress field distribution of a four-edge-clamped, transversely isotropic C/SiC plate under 168 dB traveling-wave acoustic excitation. The acoustic fatigue failure location was subsequently validated through a traveling-wave tube test. The simulation results were consistent with the experimental findings, indicating that fatigue failure first occurred in two symmetric in-plane regions with relatively high stress levels. This study provides essential technical support for stress analysis and failure-mode evaluation of composite materials under high-intensity acoustic loading.