AVIATION & AERONAUTIC CALCULATOR
Cl Max
A precise tool.
What is the Cl Max & How does it work?
The lift coefficient (Cl) is a dimensionless number that characterizes the lift generated by an airfoil section and is used in fluid dynamics to quantify the lift-generating ability of a wing or airfoil.
Maximum lift coefficient (Cl_max) occurs at the angle of attack where the lift is highest before stall. It is influenced by factors such as airfoil shape, Reynolds number, and Mach number.
Cl_{max} = frac{L_{max}}{frac{1}{2} rho V^2 S}
Cl_max = Maximum lift coefficient
L_max = Maximum lift force
rho = Air density
V = Velocity of the airfoil relative to the fluid
S = Surface area of the wing
L_max = Maximum lift force
rho = Air density
V = Velocity of the airfoil relative to the fluid
S = Surface area of the wing
Parameters
Result
β
Frequently Asked Questions
What is the formula for Cl_max?
Cl_max = Maximum lift coefficient (L_max) divided by (1/2 * Ο * V^2 * S), where L_max is maximum lift force, Ο is air density, V is velocity, and S is wing area.
How does Reynolds number affect Cl_max?
The Reynolds number influences the flow characteristics around the airfoil. Higher Reynolds numbers can lead to higher Cl_max values for some airfoils.
What factors determine the angle of attack at Cl_max?
The angle of attack at Cl_max is determined by the airfoil shape and its aerodynamic properties. Different airfoils have different optimal angles for maximum lift.
Can Mach number affect Cl_max?
Yes, Mach number can affect Cl_max, especially at high speeds where compressibility effects become significant.
How do I calculate L_max if I know Cl_max?
L_max = Cl_max * (1/2 * Ο * V^2 * S), where you multiply the maximum lift coefficient by the dynamic pressure and wing area.
Results are for informational purposes only and do not constitute professional advice.