In flight mechanics and aerodynamics, the coefficient of drag (CD) with respect to angle of attack refers to how the drag force acting on an airfoil or wing changes as the angle of attack (α) is varied.
Cn sin(alpha)+Cc cos(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.