Research Reynolds number effect correction for air supercritical laminar complex wing

Transition significantly affects aerodynamic characteristics of an airplane, such as the drag, lift and pitching moment, and the transition position of supercritical laminar complex wings is greatly influenced by Reynolds number effect. The traditional methods of Reynolds number effect correction are not suitable anymore for those aircraft with supercritical laminar complex wings. A γ-Re_θ model for the transition prediction of an airplane with supercritical laminar complex wings is introduced. The transition point could be obtained by this way according to its Reynolds number, and the computational transition points are accord with the wind tunnel tests. The wind tunnel experiment data are corrected and modified by the combination of CFD results and experiment data. The traditional Reynolds number effect correction methods correct the drag only, while this new proposed method corrects the lift, drag and pitching moment respectively and simultaneously. More accurate data for real flight could be obtained from wind tunnel experiment data by this method, and makes the flight safer.