If the speed of flow past the lower surface of an airplane wing is 101 m/s,...
If the speed of flow past the lower surface of an airplane wing is 101 m/s, what speed of flow over the upper surface will give a pressure difference of 889 Pa between upper and lower surfaces? Take the density of air to be 1.30 × 10-3 g/cm3. Assume the lower surface is at the higher pressure.
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If the speed of flow past the lower surface of an airplane wing is 101 m/s,...
Help System Announcements PRINTER VERSION BACK NEXT ES Chapter 14, Problem X6 If the speed of...
Help System Announcements PRINTER VERSION BACK NEXT ES Chapter 14, Problem X6 If the speed of flow past the lower surface of an airplane wing is 130 m/s, what speed of flow over the upper surface will give a pressure difference of 928 Pa between upper and lower surfaces? Take the density of air to be 1.30 x 10 g/cm2. Assume the lower surface is at the higher pressure. Number Units the tolerance is +/-2% Click if you would like...
A small jet airplane has a total wing area of 77.5 m2 and a mass of...
A small jet airplane has a total wing area of 77.5 m2 and a mass of 7.03 x 104 kg (a) If this jet is in horizontal flight, determine the pressure difference between the lower and upper surfaces of the wings Pa (b) When the speed of air traveling over the wing is 237 m/s, determine the speed of air under the wing. Use 1.29 kg/m3 as the density of air. m/s (c) Why do all aircraft have a maximum...
A small jet airplane has a total wing area of 62.5 m2 and a mass of...
A small jet airplane has a total wing area of 62.5 m2 and a mass of 7.03 104 kg. (a) If this jet is in horizontal flight, determine the pressure difference between the lower and upper surfaces of the wings. (b) When the speed of air traveling over the wing is 237 m/s, determine the speed of air under the wing. Use 1.29 kg/m3 as the density of air.
The total wing area of a Boeing B-29 is 1736 ft. The fully loaded take-off mass...
The total wing area of a Boeing B-29 is 1736 ft. The fully loaded take-off mass of a B-29 is 6.25 x 104 kg. The cruising speed of the B-29 is 275 mi/h. At cruising altitude, the air temperature is 251 K and the air pressure is 6.16 x 10Pa. a. Use the density form of the ideal gas law (assuming the average molar mass of the air is 0.0288 kg moll) to compute the air density at cruising altitude...
5: Problem: Consider subsonic airflow past an airplane wing. Flow speed far ahead of the wing is ...
5: Problem: Consider subsonic airflow past an airplane wing. Flow speed far ahead of the wing is Uc The flow accelerates over the wing, reaching a maximum speed of Freestream density and temperature are poo-1.20 kg/m3 and T 300 K, respectively. Compute Moo and the percentage change in temperature at the point of maximum velocity for Uo50 m/sec and for 250 m/sec M.-0. 144, decrease by 0.4%, M. 0720, decrease by 10% Answer
5: Problem: Consider subsonic airflow past an...
An airplane has a mass of 2.2×106 kg , and the air flows past the lower...
An airplane has a mass of 2.2×106 kg , and the air flows past the lower surface of the wings at 85 m/s . If the wings have a surface area of 1200 m2 , how fast must the air flow over the upper surface of the wing if the plane is to stay in the air?
A. Find the pressure difference on an airplane wing if air flows over the upper surface...
A. Find the pressure difference on an airplane wing if air flows over the upper surface with a speed of 113m/s, and along the bottom surface with a speed of 104m/s. Delta P= ? kPa B. If the area of the wing is 33m^2, what is the net upward force exerted on the wing? -Express your answer using two sig figs. F= ? kN
Find the pressure difference on an airplane wing if air flows over the upper surface with...
Find the pressure difference on an airplane wing if air flows over the upper surface with a speed of 115 m/s , and along the bottom surface with a speed of 103 m/s . Answer is in kPa. If the area of the wing is 33 m2 , what is the net upward force exerted on the wing? Express your answer using two significant figures. Answer in kN
An airplane has a mass of 2.1×106 kg , and the air flows past the lower...
An airplane has a mass of 2.1×106 kg , and the air flows past the lower surface of the wings at 96 m/s If the wings have a surface area of 1500 m2 , how fast must the air flow over the upper surface of the wing if the plane is to stay in the air? Express your answer to two significant figures and include the appropriate units.
A jet airplane in level flight has a mass of 8.62 ✕ 104 kg, and the...
A jet airplane in level flight has a mass of 8.62 ✕ 104 kg, and the two wings have an estimated total area of 95.0 m2. (a) What is the pressure difference between the lower and upper surfaces of the wings? Pa (b) If the speed of air under the wings is 229 m/s, what is the speed of the air over the wings? Assume air has a density of 1.29 kg/m3. m/s (c) Explain why all aircraft have a...
Help System Announcements PRINTER VERSION BACK NEXT ES Chapter 14, Problem X6 If the speed of flow past the lower surface of an airplane wing is 130 m/s, what speed of flow over the upper surface will give a pressure difference of 928 Pa between upper and lower surfaces? Take the density of air to be 1.30 x 10 g/cm2. Assume the lower surface is at the higher pressure. Number Units the tolerance is +/-2% Click if you would like...
A small jet airplane has a total wing area of 77.5 m2 and a mass of 7.03 x 104 kg (a) If this jet is in horizontal flight, determine the pressure difference between the lower and upper surfaces of the wings Pa (b) When the speed of air traveling over the wing is 237 m/s, determine the speed of air under the wing. Use 1.29 kg/m3 as the density of air. m/s (c) Why do all aircraft have a maximum...
The total wing area of a Boeing B-29 is 1736 ft. The fully loaded take-off mass of a B-29 is 6.25 x 104 kg. The cruising speed of the B-29 is 275 mi/h. At cruising altitude, the air temperature is 251 K and the air pressure is 6.16 x 10Pa. a. Use the density form of the ideal gas law (assuming the average molar mass of the air is 0.0288 kg moll) to compute the air density at cruising altitude...
5: Problem: Consider subsonic airflow past an airplane wing. Flow speed far ahead of the wing is Uc The flow accelerates over the wing, reaching a maximum speed of Freestream density and temperature are poo-1.20 kg/m3 and T 300 K, respectively. Compute Moo and the percentage change in temperature at the point of maximum velocity for Uo50 m/sec and for 250 m/sec M.-0. 144, decrease by 0.4%, M. 0720, decrease by 10% Answer
5: Problem: Consider subsonic airflow past an...
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