Abstract: Based on a wind-tunnel model of an elastic wing, the gust response and the load alleviation control law design using classical control theory are presented. The test is performed in the FD-09 low-speed wind tunnel with the size of 3m×3m, which is located at China Academy of Aerospace Aerodynamics. Numerical analysis and test results show that (1) the wing tip acceleration (WTA) is alleviated by 25%―35% and the wing-root bending moment (WRBM) is alleviated by 30%―40% when the air speed is 14m/s and the gust frequency ranges from 2 to 3Hz; (2) the WTA in closed-loop is alleviated by 27%―34% and the WRBM in closed-loop is alleviated by 30%―40% when the air speed ranges from 10 to 16m/s and the gust frequency is 2Hz. In this study, the alleviation effect of WTA on the low frequency has direct influence on the alleviation effect of WRBM. The error between the finite element model and the reality model causes the error between the theoretical result and test result.