It is a very good explanation. I would further the explanation of why moment remains constant in AC. If we compare 0 degree AoA to bigger AoA we can observe increase in lift and consequently, the CP also moves forward, thus reducing the x (or the "lever"). Since the moment equations is M = F * x, the increase of AoA causes the force/lift to increase but the x decreases, which is why the two moments stay the same in AP. In the first example the lift is lower but the lever is greater and in the second example it is vice versa, thus resulting in the same moment. I hope this clarifies some possible confusion.
Very good explanation, thank you. But, what is this aerodynamic useful for? Where does a shaft that holds an airfoil should be located (for VAWTs and for spoilers)?
Aerodynamic center is quite useful for stability analysis. For flying wing (wing only) configuration, CG must lie ahead of AC for a longitudinal static stability.
Good explained but I m still having doubt that Is basic it is like how does air above airfoil crowd n velocity n pressure terms and how this helps in lifting up airfoil
He got approval for his lecture at 5:52. By the way very nice presentation. Thanks alot.
It is a very good explanation. I would further the explanation of why moment remains constant in AC. If we compare 0 degree AoA to bigger AoA we can observe increase in lift and consequently, the CP also moves forward, thus reducing the x (or the "lever"). Since the moment equations is M = F * x, the increase of AoA causes the force/lift to increase but the x decreases, which is why the two moments stay the same in AP. In the first example the lift is lower but the lever is greater and in the second example it is vice versa, thus resulting in the same moment. I hope this clarifies some possible confusion.
Explanation is good but red colour script is not properly visible.
Very good explanation, thank you. But, what is this aerodynamic useful for? Where does a shaft that holds an airfoil should be located (for VAWTs and for spoilers)?
Aerodynamic center is quite useful for stability analysis. For flying wing (wing only) configuration, CG must lie ahead of AC for a longitudinal static stability.
@Alex Keti statically unstable
May I ask what book/reference you used for your discussion? Thank you
Very nice explanation
Thank you for the clear explanation
Thanks for the appreciation.
Well explained!
Hi
Request if you can use some other colour(white/yellow) for writing, as red on black background is difficult to appreciate
Thanks
Thank you so much for pointing this out. I will take care of this in new videos.
Self proclaimed best explanation 😂
Good explained but I m still having doubt that Is basic it is like how does air above airfoil crowd n velocity n pressure terms and how this helps in lifting up airfoil
Please watch this, I hope this will clarify your doubt ua-cam.com/video/tStLUqQREFQ/v-deo.html
Thank you :)
You're welcome!
it is not possible to have negative pressure
It basically means lower pressure (than the one on lower surface) on upper surface.
hii. Deepak Jain
your name is Deepak jain
there is something wrong in this explanation