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An airplane weighs 180 kN and has a wing area of 160 m2 and a mean chord of 4 m. The airfoil properties are given
An airplane weighing 28 kN, with a drag-area CDA = 5 m2, lands at sea level at 55 m/s and deploys a drag parachute 3 m in diameter. No other brakes are applied.
An airplane has a mass of 5000 kg, a maximum thrust of 7000 N, and a rectangular wing with aspect ratio 6.0. It takes off at sea level with a 60° split flap
An engineer makes careful measurements with a weir (see Sect. 10.7 later) which monitors a rectangular unfinished concrete channel laid on a slope of 1
An East Coast estuary has a tidal period of 12.42 h (the semidiurnal lunar tide) and tidal currents of approximately 80 cm/s.
An axial-flow pump delivers 40 ft3/s of air which enters at 20°C and 1 atm. The flow passage has a 10-in outer radius and an 8-in inner radius.
An axial-flow fan operates in sea level air at 1200 r/min and has a blade-tip diameter of 1 m and a root diameter of 80 cm.
An automobile has a characteristic length and area of 8 ft and 60 ft2, respectively. When tested in sea-level standard air, it has the following measured
An atomic explosion propagates into still air at 14.7 psia and 520°R. The pressure just inside the shock is 5000 psia. Assuming k = 1.4, what are the speed
Air flows past a two-dimensional wedge-nosed body as in Fig. P9.128. Determine the wedge half-angle d for which the horizontal component
Air flows steadily from a reservoir at 20°C through a nozzle of exit area 20 cm2 and strikes a vertical plate as in the flow is subsonic throughout.
Air flows through a 6-cm-diameter smooth pipe which has a 2 m-long perforated section containing 500 holes (diameter 1 mm), as in Fig.
Air flows through a converging diverging nozzle between two large reservoirs, as in Fig. P9.65. A mercury manometer reads h = 15 cm.
Air flows through a duct as in Fig, where A1 = 24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normal shock stands at section 2. Compute
Air flows under steady, approximately one-dimensional conditions through the conical nozzle in Fig If the speed of sound is approximately 340 m/s
Air flows steadily from a tank through the pipe in Fig. P9.91. There is a converging nozzle on the end. If the mass flow is 3 kg/s and the flow is choked
Air flows isentropically through a duct with To = 300°C. At two sections with identical areas of 25 cm2, the pressures are p1 = 120 kPa and p2 = 60 kPa
Air flows isentropically in a converging-diverging nozzle with a throat area of 3 cm2. At section 1, the pressure is 101 kPa, T1 = 300 K, and V1 = 868 m/s
Air, supplied by a reservoir at 450 kPa, flows through a converging-diverging nozzle whose throat area is 12 cm2. A normal shock stands where A1 = 20 cm2.
Air, equivalent to a Standard Altitude of 4000 m, flows at 450 mi/h past a wing which has a thickness of 18 cm, a chord length of 1.5 m, and a wingspan
Air, at stagnation temperature 100°C, expands isentropically through a nozzle of 6-cm2 throat area and 18-cm2 exit area
Air, at stagnation conditions of 450 K and 250 kPa, flows through a nozzle. At section 1, where the area = 15 cm2, there is a normal shock wave.
Air in a large tank at 100°C and 150 kPa exhausts to the atmosphere through a converging nozzle with a 5-cm2 throat area
An 8-inch model pump delivering water at 180°F at 800 gal/min and 2400 rpm begins to cavitate when the inlet pressure and velocity are 12 psia and 20 ft
An air tank of volume 1.5 m3 is at 800 kPa and 20°C when it begins exhausting through a converging nozzle to sea-level conditions.