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How is the lift equation useful when you are designing a wing?
Answer:
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.
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.
First answer by DrStrong.
Last edit by DrStrong.
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