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A wing will generate lift according to the following equation:
L = ½ A C ρ v²
A = wing area
C = lift coefficient
ρ = air density
v = air speed
From the equation you can see that the lift force is directly proportional to the wing area. Double the wing area and you double the lift, all else remaining equal. The lift force is also directly proportional to the lift coefficient, which is a function of the airfoil shape, angle of attack and wing aspect ratio. Lift is directly proportional the air density, so this tells you that an airplane flying at sea level can produce more lift than if flying at 18,000 feet. Lift is proportional to the square of velocity, meaning that if you fly twice as fast you will generate 4 times the lift, all else being equal.
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Why do large wings have more lift?
A wing will generate lift according to the following equation: L = ½ A C ρ v² A = wing area C = lift coefficient ρ = air density v = air speed From the equation you can see that the lift force is directly proportional to the wing area. Double the wing area and you double the lift, all else remaining equal.
How much lift will a wing generate?
A wing will generate lift according to the following equation: L = ½ A C ρ v² A = wing area C = lift coefficient ρ = air density v = air speed The lift coefficient C is a function of Angle of Attack (AOA), which is the angle between the wing's chord line and the relative wind. The greater the angle, the greater the lift coefficient up until the critical AOA where the wing begins to stall and lose lift. The lift coefficient is also a function of wing aspect ratio and will be specific to a certain airfoil shape.
What is a loss of lift?
When a wing loses lift it "stalls".
Is there a greater or lesser air pressure on top of the wing when lift occurs?
There has to be lesser air pressure on the top of the wing to provide lift.
Whats the relationship between speed and lift?
Lift is proportional to the density of the air and approximately proportional to the square of the flow speed. Lift also depends on the size of the wing, being generally proportional to the wing's area projected in the lift direction.
Why do large wings have more lift?
A wing will generate lift according to the following equation: L = ½ A C ρ v² A = wing area C = lift coefficient ρ = air density v = air speed From the equation you can see that the lift force is directly proportional to the wing area. Double the wing area and you double the lift, all else remaining equal.
How much lift will a wing generate?
A wing will generate lift according to the following equation: L = ½ A C ρ v² A = wing area C = lift coefficient ρ = air density v = air speed The lift coefficient C is a function of Angle of Attack (AOA), which is the angle between the wing's chord line and the relative wind. The greater the angle, the greater the lift coefficient up until the critical AOA where the wing begins to stall and lose lift. The lift coefficient is also a function of wing aspect ratio and will be specific to a certain airfoil shape.
What doesnt affect the amount of lift on an airplanes wing?
The best way to answer this question would be to say what does effect the lift of a wing. Pretty much the only things that effect the lift of a wing are the density of the air over the wing, the surface area of the wing, the speed of air over the wing and the angle of attack. Everything else has no effect on the amount of lift on a wing.
What is a loss of lift?
When a wing loses lift it "stalls".
What theory is used when designing the wing of an aircraft?
benouli
How does the lift from an aeroplane's wing change as it passes through a cloud?
LIFT on a wing shaped body is partially dependent on the density of the Fluid that the wing is passing through. If the Cloud is DENSER than the Air surrounding it the Wing will experience more LIFT.
What is the purpose of wing flap on a wing?
To provide the lift necessary for flight.
How do you calculate Lift in aircraft?
Lift is calculated using the following equation: L = 1/2 p V2ACL Where: L = Lift which is typically the weight of the aircraft p = air density (altitude and temperature effect this variable) V = velocity of the aircraft (this is the airspeed) A = wing area (including the section of the wing that is inside the fuselage) CL = is specific to each aircraft. This coefficient is calculated in a wind tunnel and is typically provided as a graph relative to the angle of attack.
Is there a greater or lesser air pressure on top of the wing when lift occurs?
There has to be lesser air pressure on the top of the wing to provide lift.
Whats the Mechanism of flying?
To achieve flight, a vehicle has to have an upwards force ( "Lift") greater than or equal to its weight.To produce lift force, what typically happens is that air moves over a wing that is shaped in such a way so that the air moves faster over the top, and slower over the bottom of the wing. From a law of fluid dynamics (Bernoulli's Equation), if a stream of air lowers its velocity, it will have a greater pressure. This means there is more pressure on the bottom of the wing than the top, and so it pushes up on the wing, producing lift.
What is wing loading of an aircraft?
Wing Loading is the details of the distribution of pressure on an aircraft wing. An aircraft flys by producing Lift by its wings. This lift force depends on the shape of the wing that produces high pressure on the bottom of the wing and low pressure on the top. The center of the lift is usually at the 1/4 chord or 25% of the width of the wing as measure from the leading edge. The Wing Loading can be designed to produce different Lift and ensure the aircraft will be easy to trim for level flight.
How do you get lift?
You get lift when the flow of air over the top of a wing or helicopter blade is less than the flow undr the wing, and it pushes it up
