Hi Postcard Professor. I just want to thank you for posting these videos. I'm in graduate school and preparing for my departmental qualifying exam. I never really understood airfoil theory until I watched your videos. Thank you for taking the time to post them. Really!
Why elliptical wing is given by the formula, Gama equal to Gama square root etc.... Someone help me. I mean there may be different elliptical shape wing.
Friend, didn't you mean an eliptical vorticity distribuition instead of an eliptic lift distribuition ? I'm confused, for me that's an eliptic vorticity distribuition.
as we know that lift per unit span is equal to the given expression(L= ρVΓ), so lift is proportional to circulation which causes vorticity at every vortex filament. so we can use both the terms. it means the same.
![Lifting line theory [Aerodynamics #16]](/img/1.gif)
Hi Postcard Professor. I just want to thank you for posting these videos. I'm in graduate school and preparing for my departmental qualifying exam. I never really understood airfoil theory until I watched your videos. Thank you for taking the time to post them. Really!
i did not get it from anderson book but now i understood thank you so much!
Need an explanation of general lift distribution
Why elliptical wing is given by the formula, Gama equal to Gama square root etc.... Someone help me. I mean there may be different elliptical shape wing.
Friend, didn't you mean an eliptical vorticity distribuition instead of an eliptic lift distribuition ?
I'm confused, for me that's an eliptic vorticity distribuition.
I think it must be elliptic distribution of the circulation Γ.Anyway, it is noted in the description as a vortex strength distribution.
as we know that lift per unit span is equal to the given expression(L= ρVΓ), so lift is proportional to circulation which causes vorticity at every vortex filament. so we can use both the terms. it means the same.
Need an explanation of general lift distribution
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