A Boeing 737-400 large transport-category civilian jet transport weighs 150,000 lbs on takeoff and SL ISA conditions (air density is 0.002377 slug/ft3). The airplane lifts off at 115% of the stalling airspeed and accelerates to takeoff safety speed (V2) of 163 KEAS (assume IAS = CAS = EAS). Two CFM56 high bypass turbofans produce constant flat-rated 2 x 22,500 lbs of thrust (maximum takeoff thrust) at given SL ISA altitude. Neglect maximum thrust decreases with altitude. The airplane's wing reference area is 1,200 ft2. The coefficient of drag is 0.085 in the takeoff flap configuration (with landing gears and doors retracted). Calculate the ROC (rate-of-climb) and the AOC (angle-of-climb) if both engines are operating and the airplane is flying at V2+15 (smaller AOA than at V2) knots up to 800 ft AGL. What will be ROC (fpm) and AOC (in radians, percentage, and degrees) in initial climb to 800 ft AGL if one engine fails completely during takeoff roll just before V1 and the decision is to go. Assume OEI drag coefficient of 0.110 due to the additional higher AOA (at V2), trim drag, and the inoperative jet engine wind-milling drag (drag due to any sideslip is neglected)? What is the percentage loss of climb performance in OEI case?

Options:
a) ROC: 1500 fpm, AOC: 4.5 degrees, 0.0785 radians, 78.5%
b) ROC: 1800 fpm, AOC: 6.2 degrees, 0.108 radians, 80.1%
c) ROC: 2000 fpm, AOC: 5.8 degrees, 0.101 radians, 72.3%
d) ROC: 2200 fpm, AOC: 7.3 degrees, 0.127 radians, 84.6%