Question

A small jet airplane has a total wing area of 67.5 m^{2}
and a mass of 8.03 10^{4} kg.

(a) If this jet is in horizontal flight, determine the pressure
difference between the lower and upper surfaces of the wings. in Pa
?

(b) When the speed of air traveling over the wing is 247 m/s,
determine the speed of air under the wing. Use 1.29
kg/m^{3} as the density of air. in m/s ?

(c) Which answer is correct to the question "Why do all aircraft have a maximum operational altitude?"

1.) The density of air decreases with higher altitude, which decreases the pressure difference until it cannot support the aircraft.

2.) The density of air increases with higher altitude, which increases the pressure difference until it cannot support the aircraft.

3.) The density of air increases with higher altitude, which decreases the pressure difference until it cannot support the aircraft.

4.) The density of air decreases with higher altitude, which increases the pressure difference until it cannot support the aircraft.

Answer #1

An airplane has two wings, each with area 5.00 m2, designed so
that air flows over the top of the wing at 240 m/s and underneath
the wing at 220 m/s. What is the mass of the airplane such that the
lift on the plane will support its weight, in 103 kg?. Note. Assume
the force from the pressure difference across the wings is directed
straight upward. Density of air is 1.29 kg/m3.

What is the net upward force on an airplane wing of area 21.0 m2
if the speed of air flow is 200 m/s across the top of the wing and
175 m/s across the bottom? (The density of air where the airplane
flies is ?air = 1.21 kg/m3.

An airplane has a mass of 48,000 kg, a wing area
of 300 m2, a maximum lift coefficient of 3.2, and a cruising
drag coefficient of 0.03 at an altitude of 12,000 m. Determine(a)
the takeoff speed at sea level, assuming it is 20 percent
over the stall speed, and (b) the thrust that the engines
must
deliver for a cruising speed of 900 km/h.

A cargo plane has two wings and each wing has an area of 34.15
m2. The mass of the cargo plane is 9310 kg. When the plane is
taking off, the speed of the air over the top of the wing v2 is 1.8
times air speed under the wing v1 (i.e. v2 = 1.8 v1). If v1 is the
same as the speed of the plane, what is the minimum speed of the
plane v1 to obtain enough lift...

A Boeing 747-8I aircraft has a mass of 447,700 kg. This includes
loading. The combined area of both wings is 554 m2. The cruise
speed is M0.855 (917km/h). Determine the speed of the wind above
the wing to maintain the aircraft's lift. The air density is 1.29
kg/m3.

A Boeing 747-8I aircraft has a mass of 447,700 kg. This includes loading. The combined area of both wings is 554 m2. The cruising speed is M0.855 (917 km / h). Determine the speed of the wind above the wing to maintain the aircraft's lift. The air density is 1.29 kg / m3

An Airbus A320 has a total wing surface area of 122.6m^2 and a
drag coefficient of 0.0872. In cruise, the aircraft files at 840
km/s (233m/s) at an altitude of 10,000m where the air density is
0.4135 kg/m^3. If the max engine is 100 kN engine, what percentage
of that thrust is the pilot going to be using in cruise?
*A380 has 2 engines

Water moves through a constricted pipe in steady, ideal flow. At
the lower point shown in the figure below, the pressure is 1.65 ✕
105 Pa and the pipe radius is 2.80 cm. At the higher point located
at y = 2.50 m, the pressure is 1.27 ✕ 105 Pa and the pipe radius is
1.30 cm. (a) Find the speed of flow in the lower section. m/s (b)
Find the speed of flow in the upper section. m/s (c)...

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