aeronautics15
New Member
Hello everyone,
I am trying to design a wing using NACA 6409 as my airfoil. I have calculated all the values for the 2d section. I just have to now to make a wing with a high L/D. My target is to design a wing for an aircraft moving at 20m/s at an altitude of 10,000m. So I have a couple of questions
1) How do i calculate co efficient of drag along the airfoil?
2) How do I determine the planform area needed?
3) Converting to 3d, which type of wing will be most efficient?
Thank You
I am trying to design a wing using NACA 6409 as my airfoil. I have calculated all the values for the 2d section. I just have to now to make a wing with a high L/D. My target is to design a wing for an aircraft moving at 20m/s at an altitude of 10,000m. So I have a couple of questions
1) How do i calculate co efficient of drag along the airfoil?
2) How do I determine the planform area needed?
3) Converting to 3d, which type of wing will be most efficient?
Thank You
