1.37 m, respectively. The

pressure coefficient distribution in the upper surface of the airfoil is

trapezoidal, with

in the TE, and the

pressure coefficient distribution in the lower surface fits well a sinusoidal function with period equal to 2.12 times the chord, and

amplitude 0.29, crossing the ordinate axis in the LE with the maximum possible positive slope. Please, compute the position of the pressure center of the

airfoil in % of the chord (with 5 decimals at least; you do not need to

put the "%" sign in the box for introducing the result, it only accepts a

numerical value; and please, use the comma "," as decimal separator).