CL with angle of attack calculator

CL” stands for the “Coefficient of Lift.” It is a dimensionless quantity that represents the lift generated by an airfoil or wing at a specific angle of attack. The coefficient of lift is a crucial parameter in understanding and analyzing the aerodynamic performance of an aircraft.

Cn cos(alpha)-Cc sin(alpha)

  • Cn: The normal force coefficient, which represents the lift force component perpendicular to the relative wind or airflow direction. It is the coefficient of lift (CL) of the airfoil or wing.
  • Cc: The axial force coefficient, which represents the drag force component parallel to the relative wind or airflow direction. It is the coefficient of drag (CD) of the airfoil or wing.
  • alpha (α): The angle of attack between the chord line of the airfoil (a straight line connecting the leading and trailing edges of the airfoil) and the relative wind or airflow direction.

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