Abstract: This paper introduced the design and test research of a swing type six component wind tunnel balance. Through the comparative analysis and research, we studied the results of an aircraft model tests and fluid calculation. The purpose of the study is to explore the force measuring accuracy and application effect of this wind tunnel balance, and the performance of swing type wind tunnel balance which adopted support structure. The research results show that within normal range, the designed swing type wind tunnel balances has a good applied effect, and the overall performance is stability. This research results can be used for the test of small aircraft wind tunnel.