The well-known vortex distribution method is applied to analyze the flow field around circulation controlled airfoil.
To express the effect of lift augmentation due to tangential blowing over round trailing-edge of the airfoil, a new parameter ``circulation factor`` is introduced. Circulation factor is formulated by dimensional analysis with respect to proper parameters and experimental data.
The flow field is solved by superposition of two potential flows; one due to uniform flow at angle of attack α and the other due to circulatory flow induced by tangential blowing, whose intensity is related to circulation factor and shape of airfoil.
The calculated pressure distributions and lifts are in a good agreement with experimental data in a range of moderate angle of attack and blowing momentum coefficient not involving severe separation.