Estimate the maximum range and the maximum endurance of a propeller-driven airplane with the following characteristics: empty weight 4000 lb, fuel weight 400 lb, specific fuel consumption 0.4 lb of fuel per horsepower per hour, propeller efficiency 0.8, zero-lift drag coefficient 0.03, wing area 200 ft2 , aspect ratio 7, and Oswald efficiency factor 0.85. Assume the standard sea-level conditions. Note: you may want to use some results given in section 6.14 of the textbook.