Recent content by Engineering77744

  1. Engineering77744

    Max L/D Ratio: Aircraft Drag Polar Explained

    Would like help as to the method rather than the answer please. Classes haven't been very clear therefore everything is self taught. Many thanks. ' The Drag polar for an aircraft is given by: CD = 0.025 + 0.08 C^2L What is the maximum Lift to Drag ratio '