An aerodynamic thermal test device and method using shock wave boundary layer interference

Abstract

The present invention relates to an aerodynamic thermal test device using shock wave boundary layer interference, comprising: an arc heater, a supersonic nozzle, a blunt wedge, a test model and a pneumatic actuator, wherein the arc heater is placed upstream of a wind tunnel test section, the supersonic nozzle is connected to the arc heater, the blunt wedge is connected to the pneumatic actuator and placed at the nozzle of the supersonic nozzle facing the airflow, and the test model and the supersonic nozzle are connected to the outer wall of the supersonic nozzle at a certain angle of attack; after the arc heater works, the high-temperature and high-speed airflow generated is ejected from the supersonic nozzle, and the pneumatic actuator controls the blunt wedge to be placed at the nozzle of the supersonic nozzle facing the airflow. The interference phenomenon between the shock wave generated by the blunt wedge and the high-temperature airflow and the boundary layer on the surface of the model is used to increase the surface pressure and surface heat flow in the interference area of ​​the test model, thereby achieving the purpose of improving the test simulation parameters. The invention is simple in method, the test device is mature and reliable, and the ground simulation capability of the aerodynamic thermal test can be greatly improved.

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