Student #: Duestion 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 coefficient of lift- is the position of the aerodynamic center (usually given or can be found in tables for the specific airfoil)- is the coefficient of the moment about the quarter-chord axis- is the aspect ratio of the wingGiven:- - Assuming typical values for an NACA 4412 airfoil at an angle of attack of :- (where is the chord length)- Let's assume the chord length is 1 (for simplicity, you can adjust this based on the actual chord length). Now, plug in the values: Calculate the numerator: So, Finally, Therefore, the location of the center of pressure is approximately chord lengths from the leading edge.