Student #: Question 3 (20 Points): In low speed, incompressible flow, the following experimental data are obtained for an NACA 4412 airfoil section at an angle of attack of 4^circ ,C_(1)=0.85 and c_(m,c/4)=-0.09 Calculate the location of center of pressure.

To calculate the location of the center of pressure for an airfoil section in low-speed, incompressible flow, we can use the following formula: Where:- is the location of the center of pressure- is the lift coefficient- is the center of pressure coefficient- is the chord lengthGiven:- - - (assuming the chord length is 1 for simplicity)Substituting the given values into the formula: Therefore, the location of the center of pressure is approximately 0.98 chord lengths from the leading edge.