On the Kutta Condition in Potential Flow over Airfoil

<table>Pressure coefficient distribution over a NACA 64012 airfoil at a <svg height="13.1375" id="M194" style="vertical-align:-0.17555pt" version="1.1" viewbox="0 0 13.325 13.1375" width="13.325" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
<g transform="matrix(.017,-0,0,-.017,.062,12.875)"><path d="M137 343l67 33q37 17 63 17q79 0 129.5 -53t50.5 -131q0 -92 -58 -156.5t-147 -64.5t-147 68t-58 182q0 63 17 119t43 95.5t61.5 72t69 52t67.5 31.5q62 22 128 33l6 -32q-56 -11 -108 -35q-149 -71 -184 -231zM227 337q-47 0 -95 -27q-6 -23 -6 -70q0 -93 36 -155.5
t96 -62.5q53 0 78 45.5t25 105.5q0 68 -35 116t-99 48z" id="x36"></path></g>
<g transform="matrix(.012,-0,0,-.012,8.225,4.712)"><path d="M326 255q0 -56 -41 -96t-99 -40t-99 40t-41 96t41 96t99 40t99 -40t41 -96zM274 255q0 38 -25.5 65t-62.5 27t-62.5 -27t-25.5 -65t25.5 -65t62.5 -27t62.5 27t25.5 65z" id="x2218"></path></g>
</svg> angle of attack obtained by XFLR5.</table>

Journal of Aerodynamics

On the Kutta Condition in Potential Flow over Airfoil

Figure 15