1.1 Calculate the uninstalled thrust for Example 1.1, using Eq. (1.6).

1.4 A J57 turbojet engine is tested at sea-level, static, standard-day conditions ( P ₀ = 14.696 psia, T ₀ = 518.7 R, and V ₀ = 0). At one test point, the thrust is 10,200 lbf while the airflow is 164 lbm/s and the fuel flow is 8520 lbm/h. Using these data, estimate the exit velocity V _e for the case of exit pressure equal to ambient pressure ( P ₀ = P _e).

1.8 Repeat Problem 1.7, using SI units.

1.10 Determine the takeoff speed of the HF-1 aircraft.

1.11 Determine the takeoff speed of the HP-1 aircraft at 90% of maximum gross takeoff weight.

1.14 An aircraft with a wing area of 800 ft ² is in level flight ( n = 1) at maximum C _L/ C _D. Given that the drag coefficients for the aircraft are C _{D 0} = 0.02, K ₂ = 0, and K ₁ = 0.2, find

1. The maximum C _L/ C _D and the corresponding values of C _L and C _D

2. The flight altitude [use Eqs. (1.29) and (1.30b)] and aircraft drag for an aircraft weight of 45,000 lbf at Mach 0.8

3. The flight altitude and aircraft drag for an aircraft weight of 35,000 lbf at Mach 0.8

4. The range for...