摘要：In the past years, Reynolds number (Re) effect correction is carried out by varied Re experiment. The experiment can obtain double logarithm linear curve between the least drag and Re, and the least drag in flying Re is got by linear exploration. However, Re effect exerts a great influence on transition position for laminar wing with high lift. Therefore, the lift, drag and longitudinal moment can’t be acquired by traditional Re effect correction. In this paper, the transition prediction simulations for laminar wing high lift are carried to obtain unconstrained transition position in different Re by adopting γ-Reθ transition prediction model. An agreement with experiment for transition position is achieved. According to the result of transition perdition and unconstrained transition test, Re effect correction in different height for the data of wind tunnel test is done. This method makes up for the traditional method, which Re effect correction for battle-plane is done for only drag. In present paper, Re effect correction for the lift, drag and longitudinal moment is done to acquire more accurate experimental data to ensure everything in flight.
