Hellow all,

I am working on an assignment and I need to calculate the center of pressure of an airfoil, through a numerical method (the panel method). I am getting a weird result because it gives its position on a point outside the chord for a determined angle of attack.

When I asked my professor he said that under an angle of attack near the angle of attack that makes Cl=0, it may come out that way, because the center of pressure is calculated through an expression that involves a quotient with the Cl=0 on its denominator.

I am confused because I don't know if it is just that the method fails in that case, or if it has some physical explanation.

Thanks for reading

I am working on an assignment and I need to calculate the center of pressure of an airfoil, through a numerical method (the panel method). I am getting a weird result because it gives its position on a point outside the chord for a determined angle of attack.

When I asked my professor he said that under an angle of attack near the angle of attack that makes Cl=0, it may come out that way, because the center of pressure is calculated through an expression that involves a quotient with the Cl=0 on its denominator.

I am confused because I don't know if it is just that the method fails in that case, or if it has some physical explanation.

Hellow all,

I am working on an assignment and I need to calculate the center of pressure o an airfoil, trough a numerical method (the panel method). I am getting a weird result because it gives its position on a point outside the chord for a determined angle of attack.

When I asked my professor he said that under an angle of attack near the angle of attack that makes Cl=0, it may come out that way, because the center of pressure is calculated through an expression that involves a quotient with the Cl=0 on its denominator.

I am confused because I don't know if it is just that the method fails in that case, or if it has some physical explanation.

Thanks for reading

Hellow all,

I am working on an assignment and I need to calculate the center of pressure of an airfoil, through a numerical method (the panel method). I am getting a weird result because it gives its position on a point outside the chord for a determined angle of attack.

When I asked my professor he said that under an angle of attack near the angle of attack that makes Cl=0, it may come out that way, because the center of pressure is calculated through an expression that involves a quotient with the Cl=0 on its denominator.

I am confused because I don't know if it is just that the method fails in that case, or if it has some physical explanation.

Thanks for reading