I don't understand how you can state that the mean camber line should be considered as a stream line. There is a discontinuity between the velocity upper to the airfoil and lower to the airfoil, induced by the vortex distribution. So the mean camber line can't be a stream line and cannot be a part of the flow field. Don't you agree?
For certain circumstances i had to choose EEE. But i want to learn about Aerospace engineering and make Fixed-wing UAV. Sir, would you help me? And suggest me some books so that i can still touch my dream 😅.
Great job explaining as always, I have taken the basics of Aerodynamics course on your website before. I only have a problem understanding how and why does the behavior of vortex sheet equate to behavior of a thin airfoil. Inspiration for this approximation had to come from somewhere I guess, and it is not fully apparent to me where did it come from and why should these two things be (to some extent) equivalent. In other words - why is there some vortex sheet distribution that can to some degree approximate a behavior of a certain airfoil.
Great question. The idea is that a thin airfoil in the limit as the thickness goes to zero, is simply a camber line. So for thin airfoils, we can approximate the airfoil by only looking at the camber line. Below stall, that camber line will be a streamline of the flow. So we replace the camber line with a sheet of vorticity. We tune the strength of the vorticity along the sheet to force the flow to align with the airfoil camber line. This makes the flow take on the shape of the camber line, and makes the camber line a streamline of the flow. Does that help?
Hi, in which video did you / do you derive the Biot-Savert expression for Vy? You mention a previous video I think, but that doesnt appear to be in this playlist.
Swaraj - thanks for the comment. I agree this video doesn't inspire students to go beyond the book's knowledge at first. However, in order to go beyond the book's knowledge, a student must first understand the basic theory. The purpose of these videos is to present that basic theory. Hopefully through the development the student can see room for improvement and bring new ideas to the table.
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At uni, we got given the final equation and then got asked to go derive it ourselves. couldn't have done it without this video. Thanks :)
Glad to hear!
Thank you!! This is better explained than how my professor, teaches this
at 14:43, you can also put: Vinfinity*sin(phi-alpha)=Vn exactly.
Thanks, really helped
I don't understand how you can state that the mean camber line should be considered as a stream line. There is a discontinuity between the velocity upper to the airfoil and lower to the airfoil, induced by the vortex distribution. So the mean camber line can't be a stream line and cannot be a part of the flow field. Don't you agree?
At 15:05 i lost you, please can you tell me where to look for this part
Thanks, amazing video, well explained
Thank you sir.
For certain circumstances i had to choose EEE. But i want to learn about Aerospace engineering and make Fixed-wing UAV.
Sir, would you help me? And suggest me some books so that i can still touch my dream 😅.
at 9:42 how u multiply by tanphi only specific terms
Great job explaining as always, I have taken the basics of Aerodynamics course on your website before.
I only have a problem understanding how and why does the behavior of vortex sheet equate to behavior of a thin airfoil.
Inspiration for this approximation had to come from somewhere I guess, and it is not fully apparent to me where did it come from and why should these two things be (to some extent) equivalent.
In other words - why is there some vortex sheet distribution that can to some degree approximate a behavior of a certain airfoil.
Great question. The idea is that a thin airfoil in the limit as the thickness goes to zero, is simply a camber line. So for thin airfoils, we can approximate the airfoil by only looking at the camber line. Below stall, that camber line will be a streamline of the flow. So we replace the camber line with a sheet of vorticity. We tune the strength of the vorticity along the sheet to force the flow to align with the airfoil camber line. This makes the flow take on the shape of the camber line, and makes the camber line a streamline of the flow. Does that help?
Thank you for this video!
You bet!
Hi, in which video did you / do you derive the Biot-Savert expression for Vy? You mention a previous video I think, but that doesnt appear to be in this playlist.
I think you're looking for this video: th-cam.com/video/vpuQa7tOCEk/w-d-xo.html
video is undoubtedly good, but we are not aspired to go beyond the book's knowledge.
Swaraj - thanks for the comment. I agree this video doesn't inspire students to go beyond the book's knowledge at first. However, in order to go beyond the book's knowledge, a student must first understand the basic theory. The purpose of these videos is to present that basic theory. Hopefully through the development the student can see room for improvement and bring new ideas to the table.