Drag Polar
![Drag and lift coefficients for NACA 633618 airfoil. Full curves are lift, dashed drag; red curves have Re = 9·106, blue 3·106.](/Images/godic/202501/10/CL,_CD_NACA6326181111.png")
![Drag polar for the NACA 633618 airfoil, colour-coded as opposite plot.](/Images/godic/202501/10/DragPolarNACA6336181112.png")
![Drag polar for light aircraft. CD0= 0.017, K = 0.075 and CL0 = 0.1. The tangent gives the maximum L/D point.](/Images/godic/202501/10/DargPolarAL1112.png")
![PR curve for the light aircraft with the drag polar above and weighing 2000 kg, with a wing area of 15 m² and a propeller efficiency of 0.8.](/Images/godic/202501/10/PRplot1112.png")
The Drag Polar is the relationship between the lift on an aircraft and its drag, expressed in terms of the dependence of the lift coefficient on the drag coefficient. It may be described by an equation or displayed in a diagram called a polar plot.