Abstract: A method is presented for correcting Reynolds number effects induced by the scale-factor in transonic 2一D airfoil testings, based on the transonic perturbation theory and boundary layer equations.The method is able to extrapolate the experimental data acquired in testings with the order of million of Re numbers to those corresponding to order of ten millions.And a comparison is made of the extrapolated data with those obtained directly in high-Re test-ing facilities,from which it can be seen that the results presented are satisfactory。

Key words: transonic flow, wind tunnel tests. Reynolds number, correction