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IF angle of attack is zero degree,is that possible to produce lift?

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Aerodynamics, General Aviation

IF angle of attack is zero degree,is that possible to produce lift?

according to the formula of lift=1/2*CL*d*S*v^2,and CL is relate to the angle of attack,if AOA is zero,than lift=0?I've doing some research of google, and said lift will be zero if aoa is zero,but that is for symmetric airfoil not asymmetric airfoil,I really confuse.

ok,if cessna 172 is at zero aoa,according to Bernoulli principle ,,upper camber have faster speed of airflow and lower pressure;than lower camber have slower speed of airflow and higher pressure,than produce lift.

So is that mean even the cessna 172 is at zero aoa,airplane still have lift?

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4 Answers



  1. Dmitriy on Feb 23, 2015

    The coefficient of lift (CL) is affected by many factors, not just angle of attack. Angle of attack is simply the primary factor in which we as pilots can CONTROL in the coefficient.

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  2. Dmitriy on Feb 23, 2015

    Basically, to further on what I was saying, the coefficient of lift is also affected by airfoil symmetry, airfoil camber, and the coefficient itself again changes when you actually practically apply an airfoil to a wing or rotor (so wing planform on a fuselage has some sort of an effect itself).

    Basically, what it comes down to is, there are lots of small factors that affect lift. In order to not make the lift formula so overly complex, instead the additional factors of lift are simplified into a single coefficient, affected by many factors. Otherwise the lift equation is derived from a simple dynamic pressure equation (I can help more on that if you’re curious too).

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  3. Brian on Mar 01, 2015

    Anrie, your analysis is spot on. Look at symmetrical airfoils. Look up “zero lift angle of attack” and you’ll find it occurs at a negative wing angle of attack in most aircraft. Nice job connecting those ideas.

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  4. Andre Alexis C. Dubouzet on Apr 17, 2015

    The pressure differential on the wings of the aircraft is what generates the lift. Notice that the wings are designed in such a way that the upper camber have a much “curved” surface than the lower camber causing a greater pressure thus generating lift. At zero AOA, because of the wing design, the wings are still generating lift but not as much as when AOA is positive.

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