The F/A-18 has two GE-404 low bypass ratio turbofan engines which produce 11,000
lb of thrust each and 17,000lbs with afterburners. The wing area is 410 ft2, the span is 40.33
ft and it weighs 40,000 lbs in its air-to-air combat configuration. The zero lift drag coefficient,
CD0 = 0.0239 and drag due to lift parameter K = 0.094. The maximum lift coefficient, CLmax =
0.88. The maximum structural load factor is 7.5 g’s. Assume afterburners are engaged for
these calculations.
a. The pilot initiates a level turn at both sea level and at 30,000 ft, plot the maximum
load factors subject to the three constraints as a function of velocity.
b. Compute the minimum turn radius and maximum turn rate subject to the three load
factor constraints for sea level and 30,000 ft and plot as a function of velocity
c. The pilot initiates a maximum load factor turn at sea level ft at the “cornering
speed” i.e. the speed at which both the maximum lift constraint and the structural
constraint are active. Find the cornering speed in knots.