Abstract: A method is developed for obtaining uniformly valid solutions about thin airfoils with blunt noses in transonic flows. The method is based on the principles of singular perturbation theory and applied to nonlifting problems. The method corrects transonic small perturbation theory which is invalid in the nose region. The first order potential equation, applicable to Inne-inner（nose）region, and the anylitic solution of which are given for the first time. A composite solution, which is uniformly valid, is constructed. Application of the method is presented for the NACA0012 airfoil. Comparison of the results with those of the full potential equation shows in good agreement.