Abstract: In order to meet the need of high-Mach number scramjet development, the scramjet thrust test technique in the shock tunnel is studied. A piezoelectric balance is used to test the scramjet thrust in the shock tunnel. The research includes the balance design, calibration and thrust test in the shock tunnel. The finite element analysis method is used in the balance design to optimize the balance structure. The simulation results show that the sensitivity of the balance can reach 17.447 mV/N, and the first-order frequency mode can reach 1022.40 Hz. The validation test is conducted in the shock tunnel with the fuel and without the fuel injection. The test results show that, the difference of the drag force is about 220 N between two different experimental conditions. Which means the thrust of the scramjet under different conditions can be distin-guished with the new developed balance.