Flutter divergence can cause catastrophic damage to aircraft structure. To mitigate the hazards associated with flutter, it is essential to conduct research on this phenomenon, with wind tunnel testing being a critical method of investigation. This paper presents a series of flutter tests conducted in a one-meter scale high-speed wind tunnel using a typical delta wing model. A flutter test support device and a model protective cover were designed to assess the interference of the support device on the model’s flutter mode and to evaluate the effectiveness of the protective cover in safeguarding the model within a high-speed airflow. The results indicate that the wind tunnel used in this study is capable of conducting flutter tests, and the test results are clear and usable. The sensor data and non-contact measurement data can mutually corroborate each other. The test method designed in this paper can guide future flutter tests for more components and under more complex conditions. The data obtained can serve as a reference for aircraft flutter design.