Abstract: The carbon fiber toughened silicon carbide matrix composite(C/SiC) used in aircraft structure will be in a severe aerodynamic thermal-acoustic environment during the flight, which might damage the structure. Therefore, it is necessary to conduct the thermal-acoustic test in the laboratory. In this paper, an progressive wave tube is used for the thermal-acoustic test of a typically-configured C/SiC skin frame specimen. The detailed experimental set-up and the test method are given. From the valid test data, the failure mode of the specimen is identified, and the thermal noise environmental adaptability of the configuration part is validated.