Lift and Drag Calculator
Calculate aerodynamic forces for your aircraft or vehicle design
kg/m³
m/s
m²
(dimensionless)
(dimensionless)
Results
Lift Force (L):
0 N
Drag Force (D):
0 N
Lift-to-Drag Ratio (L/D):
0
Formulas Used
Lift Force (L) = ½ × ρ × V² × A × CL
Drag Force (D) = ½ × ρ × V² × A × CD
Lift-to-Drag Ratio = CL / CD
Drag Force (D) = ½ × ρ × V² × A × CD
Lift-to-Drag Ratio = CL / CD
Frequently Asked Questions
What is lift force in aerodynamics?
Lift force is the component of the aerodynamic force that is perpendicular to the relative wind and opposes the weight of the aircraft, enabling flight. It’s generated primarily by the wings as air flows over and under them.
What factors affect drag coefficient?
The drag coefficient is influenced by the shape of the object (streamlined vs. blunt), surface roughness, Reynolds number (which depends on velocity and size), Mach number (for high speeds), and the angle of attack for airfoils.
What is a good lift-to-drag ratio?
For commercial airliners, typical L/D ratios range from 15:1 to 20:1. Gliders can achieve much higher ratios (50:1 or more). Fighter aircraft typically have lower ratios (around 10:1) due to their need for maneuverability over efficiency.
How does altitude affect lift and drag?
As altitude increases, air density decreases. This reduces both lift and drag forces for a given velocity. Aircraft must fly faster at higher altitudes to maintain the same lift. The coefficients (CL and CD) remain unchanged if the angle of attack is constant.