def drag_total(state,settings,geometry):
    """Extract the drag coefficient

    Assumptions:
    None

    Source:
    N/A

    Inputs:
    state.conditions.aerodynamics.drag_coefficient [Unitless]

    Outputs:
    CD (coefficient of drag)                       [Unitless]

    Properties Used:
    N/A
    """  
    
    CD = state.conditions.aerodynamics.drag_coefficient     
    
    return CD