For these problems, you will consider an aircraft's range and performance utilizing the Breguet range equation...

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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=CD0 + KCL CDO = 0.0179 k = 0.0427 S = 1,341 ft 1. (25%) Consider a battery powered Boeing 737-700 with a cruise weight 160,000 lb. Of this, 80,000 lb is empty weight, 40,000 lb is battery weight, and 40,000 lb is payload. Let the total efficiency (including battery, transmission, electronics, motor, and propulsive efficiencies) of the all-electric drive train be 60% and the specific power of the battery be 300 Wh/kg. Assume this is a power-rated system. Given this, estimate: a. The range on a full charge with a full payload. b. The range on a full charge with a half payload. c. The necessary energy (in Wh) for a mission of 100 nautical miles of range. 2. (25%) Consider a conventional, fossil-fuel burning Boeing 737-700 with a cruise weight 160,000 lb. Of this, 80,000 lb is empty weight, 40,000 lb is fuel weight, and 40,000 lb is payload. Assume the aircraft maintains a constant velocity and has an initial altitude of 30,000 feet. Take CT to be 0.0003 lbf/lb/sec. This is a thrust-rated system. Given this, estimate: a. The range on a full tank of fuel with a full payload. b. The range on a full tank of fuel with a half payload. c. The necessary fuel weight for a mission of 1,000 nautical miles of range. 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. 11gt = 60% ngb= 1 1p = 65% Q = 0.5 ef = 43 MJ/kg ebatt = 300 Wh/kg nem = 90% 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=CD0 + KCL CDO = 0.0179 k = 0.0427 S = 1,341 ft 1. (25%) Consider a battery powered Boeing 737-700 with a cruise weight 160,000 lb. Of this, 80,000 lb is empty weight, 40,000 lb is battery weight, and 40,000 lb is payload. Let the total efficiency (including battery, transmission, electronics, motor, and propulsive efficiencies) of the all-electric drive train be 60% and the specific power of the battery be 300 Wh/kg. Assume this is a power-rated system. Given this, estimate: a. The range on a full charge with a full payload. b. The range on a full charge with a half payload. c. The necessary energy (in Wh) for a mission of 100 nautical miles of range. 2. (25%) Consider a conventional, fossil-fuel burning Boeing 737-700 with a cruise weight 160,000 lb. Of this, 80,000 lb is empty weight, 40,000 lb is fuel weight, and 40,000 lb is payload. Assume the aircraft maintains a constant velocity and has an initial altitude of 30,000 feet. Take CT to be 0.0003 lbf/lb/sec. This is a thrust-rated system. Given this, estimate: a. The range on a full tank of fuel with a full payload. b. The range on a full tank of fuel with a half payload. c. The necessary fuel weight for a mission of 1,000 nautical miles of range. 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. 11gt = 60% ngb= 1 1p = 65% Q = 0.5 ef = 43 MJ/kg ebatt = 300 Wh/kg nem = 90%