Wind tunnel experiment system for free flight model

The invention provides a wind tunnel experiment system for an aircraft, which is used for wind tunnel experiments of free flight models and can simulate a real state of an airplane lengthways and freely flying. The system comprises a wind tunnel experiment model for the aircraft, a stability control system and a support system, wherein the stability control system is connected with the wind tunnel experiment model through a signal line, and is used for receiving built-in sensor signals of the model and outputting control surface deflection signals through corresponding control operation. Therefore, various wind tunnel experiment researches on the aircrafts (such as wind tunnel experiment researches on flutter models, wind tunnel experiment researches on full aircraft flight mechanics, wind tunnel experiment researches on full aircraft gust alleviation, wind tunnel experiment researches on full aircraft control augmentation stability systems and the like) can be realized.