Lift coefficient for steady level flight based on weight Calculator

The lift coefficient (“CL”) for steady level flight is a dimensionless parameter that quantifies the relationship between the lift generated by an aircraft’s wings and the dynamic pressure of the surrounding airflow. In steady level flight, the lift force produced by the wings is equal to the weight of the aircraft, allowing it to maintain a constant altitude. 

NOTE: The highlighted formula is the used one.

• CL is the Lift coefficient
• W is the weight of the aircraft 
• q∞ is the Dynamic pressure 
• S is the Wing Area