For these problems, you will consider an aircraft's range and performance utilizing the Breguet range equation for a Boeing 737-700 sized aircraft. We will assume constant aerodynamic performance as specified by the drag polar below. Assume a cruise altitude of 30,000 feet, a cruise speed of Mach 0.82, and disregard any reserve requirements or energy expenditure to get to cruising altitude. Aircraft Drag Polar CD = CDO +kC C'DO = 0.0179 k = 0.0427 S = 1,341 ft 3. (50%) Now consider a parallel battery-turbine hybrid-electric aircraft. This aircraft has a cruise weight 160,000 lb. Of this, 80,000 lb is empty weight, 20,000 lb is battery weight, 20,000 lb is fuel weight, and 40,000 lb is payload. Using the methodology found here: https://www.mdpi.com/2226-4310/10/8/687 and the values in the table below, apply equation 41 to find (BE CAREFUL WITH YOUR UNITS!): a. The range on a full tank of fuel and a fuel with a full payload. b. The range on a half charge of the battery with a full tank of fuel with a half payload. ngt=60% ngb = 1 np = 65% Q=0.5 ef = 43 MJ/kg ebatt 300 Wh/kg nem = 90%