air (density=1.290 kg/m3) passes over the top and bottom surfaces of an aircraft's wing at speeds...
air (density=1.290 kg/m3) passes over the top and bottom surfaces of an aircraft's wing at speeds of 981.0 km/h and 558.0 km/h respectively. what is the lift in newton's due to the bernoulli effect on the wings of total cross-sectional area of 80.25m2? what is the maximum amount of stuff (in kg) can the plane handle on account of this effect?
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air (density=1.290 kg/m3) passes over the top and bottom
surfaces of an aircraft's wing at speeds...
An airplane wing generates lift due to a difference in air speed above and below the...
An airplane wing generates lift due to a difference in air speed above and below the wing. If the wings are both at the same height, what term is the same on both sides of the Bernoulli equation? Calculate the change in pressure (P-bottom - P_top) a wing experiences if the air moves at 245 m/s above the wing and 222m/s below the wing. The density of air is 1.29kg/m^3. Calculate the lift force the plane experiences if it has...
What is the lift (in newtons) due to Bernoulli's principle on a wing of area 88m2...
What is the lift (in newtons) due to Bernoulli's principle on a wing of area 88m2 if the air passes over the top and bottom surfaces at speeds of 280 m/s and 150 m/s, respectively.
An air-plane has an effective wing surface area of 12.0 m² that is generating the lift...
An air-plane has an effective wing surface area of 12.0 m² that is generating the lift force. In level flight the air speed over the top of the wings is 65.5 m/s, while the air speed beneath the wings is 39.0 m/s. What is the weight of the plane?(The density of air is 1.29 kg/m³)
8. An air-plane has an effective wing surface area of 14.0 m² that is generating the...
8. An air-plane has an effective wing surface area of 14.0 m² that is generating the lift force. In level flight the air speed over the top of the wings is 60.5 m/s, while the air speed beneath the wings is 38.5 m/s. What is the weight of the plane?(The density of air is 1.29 kg/m³)
A U-tube contains liquid of unknown density. An oil of density 770 kg/m³ is poured into...
A U-tube contains liquid of unknown density. An oil of density
770 kg/m³ is poured into one arm of the tube until the oil column
is 13.5 cm high. The oil-air interface is then 4.5 cm above the
liquid level in the other arm of the U-tube. Find the density of
the liquid.
A raft is made of 11 logs lashed together. Each is 38.0 cm in
diameter and has a length of 7.00 m. How many people (whole number)...
Air streams horizontally past a small airplane's wings such that the speed is 70.0 m/s over...
Air streams horizontally past a small airplane's wings such that the speed is 70.0 m/s over the top surface and 60 m/s past the bottom surface. If the density of air is 1.20 kg/m^3, what is the lift due to pressure difference on the wing, assumed to be very thin and having an area 16.2 m^2 ? If you wanted to calculate the net lift on the wing using only the physics learnt in this class, what other data value(s)...
Problem III A small airplane has a total mass of 1800 kg and a wing area...
Problem III A small airplane has a total mass of 1800 kg and a wing area of 42 m2. While cruising at arn altitude of 4000 m at a constant speed of 280 km/h this airplane generate 190 kW of power. At this altitude he air density ρ-0.82 kg/m3 a) Determine the thrust developed by this airplane b) Determine the lift and drag coefficients of this airplane
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the dens...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
A 4.00 cm x 4.00 cm x 4.00 cm cube of density 920 kg/m3 is floating at rest at the top of a beaker of cross sectional area 100 cm2 with 500 mL of water in it. 500 mL of oil of density 900 kg/m3 is add...
A 4.00 cm x 4.00 cm x 4.00 cm cube of density 920 kg/m3 is floating at rest at the top of a beaker of cross sectional area 100 cm2 with 500 mL of water in it. 500 mL of oil of density 900 kg/m3 is added to the top of the beaker, and the cube is observed to float completely submerged, unevenly straddling the boundary between the oil and water. a. Draw a picture showing the beaker, layers of...
An enclosed tank containing water of density (r = 1000 kg/m3) has a hole in its side at a distance y1 from the tank’s bottom as shown in figure. The hole is open to atmosphere (Po = 1´105 Pa) , and it...
An enclosed tank containing water of density (r = 1000 kg/m3) has a hole in its side at a distance y1 from the tank’s bottom as shown in figure. The hole is open to atmosphere (Po = 1´105 Pa) , and its diameter is much smaller than the diameter of the tank. The air above the liquid is maintained at a pressure (P = 1.6´105 Pa). Determine the speed of the liquid as it leaves the hole when the liquid’s...
An airplane wing generates lift due to a difference in air speed above and below the wing. If the wings are both at the same height, what term is the same on both sides of the Bernoulli equation? Calculate the change in pressure (P-bottom - P_top) a wing experiences if the air moves at 245 m/s above the wing and 222m/s below the wing. The density of air is 1.29kg/m^3. Calculate the lift force the plane experiences if it has...
A U-tube contains liquid of unknown density. An oil of density
770 kg/m³ is poured into one arm of the tube until the oil column
is 13.5 cm high. The oil-air interface is then 4.5 cm above the
liquid level in the other arm of the U-tube. Find the density of
the liquid.
A raft is made of 11 logs lashed together. Each is 38.0 cm in
diameter and has a length of 7.00 m. How many people (whole number)...
Air streams horizontally past a small airplane's wings such that the speed is 70.0 m/s over the top surface and 60 m/s past the bottom surface. If the density of air is 1.20 kg/m^3, what is the lift due to pressure difference on the wing, assumed to be very thin and having an area 16.2 m^2 ? If you wanted to calculate the net lift on the wing using only the physics learnt in this class, what other data value(s)...
Problem III A small airplane has a total mass of 1800 kg and a wing area of 42 m2. While cruising at arn altitude of 4000 m at a constant speed of 280 km/h this airplane generate 190 kW of power. At this altitude he air density ρ-0.82 kg/m3 a) Determine the thrust developed by this airplane b) Determine the lift and drag coefficients of this airplane
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
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