1. 6 points The Lockheed L-1011 TriStar is an airliner with three engines, including one mounted on the tail, as seen in Fig 1 (left). A simplified schematic of the tail-mounted engine is shown on the right. The TriStar cruises at an altitude of 30 000 ft at a speed of V = 270 m/s. The freestream pressure and density at this altitude are p = 30 kPa and p1 0.4kg/m respectively. Fuel enters the engine at the rate of 0.74 kg/s. The combustion byproducts/air mixture exits the nozzle at a density of p2 = 0.44 kg/m and pressure p2 = 48 kPa. The circular inlet and outlet have diameters D = 3.10 m and D = 2.25 m respectively. Calculate the thrust produced by this engine, Fr, under these conditions. TWA = V P1 P1 Inlet D m "fuel D2 V2 P2 P2 Outlet Engine Figure 1: (Left) A TriStar in flight Jon Proctor; and (Right) A simplified view of the tail-mounted engine.