Problem 4 - Fluids, lift-force, and Stevin's law. (a) An airplane has a total wing area A = 500 m². As the airplane moves, the average air speed just above the wings, Vtop, is twice as large as the average air speed just below the wings, Vbot. If the total mass of the airplane, cargo and passengers included, is mtot 3x105 kg, estimate (one significant digit) the airplane speed v = (Vtop+ Voot)/2 at take-off from sea level. (b) Using Stevin's law in the atmosphere, and assuming that air density is proportional to air pressure, estimate (one significant digit) the speed that the airplane must maintain when flying at an altitude h=7800 m. (c) Assuming that the maximum speed that the plane can reach is Vmax = 1200 km/h, estimate the maximum altitude that the plane can reach. In (b) and (c), assume that the total mass and other = parameters the same as in (a). (Hint: use air density = 1.3 kg/m³ at sea level, In(2) ≈ 0.7 and √√e = eo= 1.6).

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I need explanation for part b and c 

part a answer is 300km/h

part b answer 480 km/h

Part c answer 22000 m

Problem 4 - Fluids, lift-force, and Stevin's law.
(a) An airplane has a total wing area A = 500 m². As the airplane moves, the average air speed just above
the wings, Vtop, is twice as large as the average air speed just below the wings, Vbot. If the total mass
of the airplane, cargo and passengers included, is mtot 3x105 kg, estimate (one significant digit) the
airplane speed v = (Vtop+ Voot)/2 at take-off from sea level.
(b) Using Stevin's law in the atmosphere, and assuming that air density is proportional to air pressure,
estimate (one significant digit) the speed that the airplane must maintain when flying at an altitude
h=7800 m.
(c) Assuming that the maximum speed that the plane can reach is Vmax = 1200 km/h, estimate the
maximum altitude that the plane can reach. In (b) and (c), assume that the total mass and other
=
parameters the same as in (a). (Hint: use air density = 1.3 kg/m³ at sea level, In(2) ≈ 0.7 and √√e =
eo=
1.6).
Transcribed Image Text:Problem 4 - Fluids, lift-force, and Stevin's law. (a) An airplane has a total wing area A = 500 m². As the airplane moves, the average air speed just above the wings, Vtop, is twice as large as the average air speed just below the wings, Vbot. If the total mass of the airplane, cargo and passengers included, is mtot 3x105 kg, estimate (one significant digit) the airplane speed v = (Vtop+ Voot)/2 at take-off from sea level. (b) Using Stevin's law in the atmosphere, and assuming that air density is proportional to air pressure, estimate (one significant digit) the speed that the airplane must maintain when flying at an altitude h=7800 m. (c) Assuming that the maximum speed that the plane can reach is Vmax = 1200 km/h, estimate the maximum altitude that the plane can reach. In (b) and (c), assume that the total mass and other = parameters the same as in (a). (Hint: use air density = 1.3 kg/m³ at sea level, In(2) ≈ 0.7 and √√e = eo= 1.6).
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