Airfoil Lift and Drag Calculator (XFOIL)
This calculator helps aerospace engineers and enthusiasts to compute the lift and drag coefficients of an airfoil using XFOIL data. It assists in optimizing airfoil performance under various conditions.
Calculator
Results
Lift Coefficient (Cl):
N/A
Drag Coefficient (Cd):
N/A
Data Source and Methodology
All calculations are based on the XFOIL aerodynamic data. For more information, visit Airfoil Tools.
The Formula Explained
The lift and drag coefficients are calculated using the following formulas:
Cl = 2π * α (in radians)
Cd = Cl² / (π * AR)
Glossary of Variables
- Speed: The velocity of the airfoil relative to the air.
- Angle of Attack (α): The angle between the airfoil's chord line and the oncoming air.
- Air Density: The mass per unit volume of the air.
Frequently Asked Questions (FAQ)
What is an airfoil?
An airfoil is a shape designed to generate lift when air flows over it.
How is lift generated?
Lift is generated by the difference in pressure between the upper and lower surfaces of the airfoil.
Why is angle of attack important?
The angle of attack affects the lift generated by the airfoil.
What factors influence drag?
Drag is influenced by the airfoil shape, surface roughness, and angle of attack.