Why does a perpendicular airflow increase the parasitic drag? You actually have a longer length over which the drag occurs on the tapper wing (for the same wing span). Is the drag from tip vortices reduced due to the higher aspect ratio near the wing tip?
Fair enough as far as it goes - but wing design isn't all about aerodynamics when it comes to plan form. Inherent strength and consequent weight are equally, sometimes more, important. All forms of tapered or quasi-elliptical wings reduce maximum bending moment, increase bending strength and hence are most commonly used. Parallel wings delivering maximum lift usually need some form of structural intervention (struts) to produce a structurally efficient package, [A retired aircraft stress engineer]
@@sfzdgxfhycgjuvkyihopu For example, in plan-form: from the root of a 3m chord, a 10m leading edge radius, a 10m trailing edge radius and at the point of intersection a 0.5m blending radius. Look at the cross section of any large European petrol tanker. It will be a 3m top and bottom radius blended with a 2m side radius: nominally elliptical.
I suspect “as far as it goes” in this video was just the very beginning of a much longer, multi-topic discussion. This was just a teaser for courses at the web site.
I cannot wait until someone designs the first true variable geometry wing capable of automatically changing its shape to suit different types of flying. Utilizing shape memory alloys and polymers, or maybe even artificial muscles.
Elliptical Planforms make approximately the same span wise lift distribution as the planform. Which may be "good" but is not ideal. A Bell shaped span wise lift distribution is actually ideal. Prandtl knew this back in the 30's.
there is a video made by Real Engineering and another one made by Millenium 7* that are very good to understand why it's such a controversial design. You can just search it on yt (I'm too lazy to link them lol)... but to sum it up, basically: the airflow impacts the wing from the tip, and then goes towards the root. What this means is that the stall will occur from the root of the wing, and then it will proceed outwards to the tip. This is very good at slow speeds and high angles of attack. However, when going at higher speeds, especially supersonic ones, the bending and twisting solicitations the wing is subject to become a big problem, along with drag, which is much greater.
Wonder if there's a wing design that allows for both high speeds, maneuverability, and short take offs/landings. Like a swept wing... idk carbon cub? lol
Pretty much the only valid reason for wing sweep is to allow thicker wing sections to be flow at higher speeds than their critical Mach numbers for their respective thick-airfoil sections. e.g. an Airfoil that is 14% thickness to chord (height to length) might have a critical Mach number of 0.68 (68% the speed of sound). And an 9% Airfoil might have a critical mach number of 0.85. But a highly swept 14% thick Airfoil, which has more internal volume for structure and fuel, can attain the same Mach number speeds as a 9% Airfoil which has no sweep.
@@ChrisZoomER given this comment is 9 months old I think you might've watched that too, but there is also another video about forward swept wings, made by Real Engineering... and also one made by Millenium 7*
Must consider the economic aspects for leisure and commercial missions as well as the speed/altitude regime they will work on. Swept planforms and elliptical cost much more. Swept wings do not have good handling characteristics. Swept wings and swept tail feathers are actually worse performers at subsonic speeds under, say, Mach 0.6. For military applications, the price is of no consideration vs air superiority. Neither is the handling, unless you believe there will be dogfights in the future (highly unlikely, but possible)
Наука
Right when it starts to get good, the video ends. 😳
done by a porn director
Agreed. That ending came outta nowhere.
Ikr, he was still talking. They want you to buy the course for the whole thing I’m sure
Took this ground school course for my PPL and it was amazing. Highly recommend it.
Fr
Great training series, worth the money for a super ground school….. I used it and loved it 🇨🇦🍻
Nice explanation of planform. I appreciate the video.
helped me very well . Thanks.
Why does a perpendicular airflow increase the parasitic drag? You actually have a longer length over which the drag occurs on the tapper wing (for the same wing span). Is the drag from tip vortices reduced due to the higher aspect ratio near the wing tip?
They offer a great ground school 🇨🇦👍🍻
Thanks Great Video
It’s 11:33 pm and I’m studying for my CFI and it cuts off right when it gets good noo!
Fair enough as far as it goes - but wing design isn't all about aerodynamics when it comes to plan form. Inherent strength and consequent weight are equally, sometimes more, important. All forms of tapered or quasi-elliptical wings reduce maximum bending moment, increase bending strength and hence are most commonly used. Parallel wings delivering maximum lift usually need some form of structural intervention (struts) to produce a structurally efficient package, [A retired aircraft stress engineer]
What is QUASI-elliptical???
@@sfzdgxfhycgjuvkyihopu For example, in plan-form: from the root of a 3m chord, a 10m leading edge radius, a 10m trailing edge radius and at the point of intersection a 0.5m blending radius. Look at the cross section of any large European petrol tanker. It will be a 3m top and bottom radius blended with a 2m side radius: nominally elliptical.
I suspect “as far as it goes” in this video was just the very beginning of a much longer, multi-topic discussion. This was just a teaser for courses at the web site.
Thks
I cannot wait until someone designs the first true variable geometry wing capable of automatically changing its shape to suit different types of flying. Utilizing shape memory alloys and polymers, or maybe even artificial muscles.
Elliptical Planforms make approximately the same span wise lift distribution as the planform. Which may be "good" but is not ideal. A Bell shaped span wise lift distribution is actually ideal. Prandtl knew this back in the 30's.
👌👌👌
Really good video. Basic but not eli5 +1
so here is a question. Is it the wing that makes the Diamond DA-40 (ft. in the intro) "safer" than other airplanes like Cessna 175s and S22?
It does not. Diamond safety is about the same as any light airplane.
What about a forward style swept wing?
there is a video made by Real Engineering and another one made by Millenium 7* that are very good to understand why it's such a controversial design. You can just search it on yt (I'm too lazy to link them lol)... but to sum it up, basically: the airflow impacts the wing from the tip, and then goes towards the root. What this means is that the stall will occur from the root of the wing, and then it will proceed outwards to the tip. This is very good at slow speeds and high angles of attack. However, when going at higher speeds, especially supersonic ones, the bending and twisting solicitations the wing is subject to become a big problem, along with drag, which is much greater.
Wonder if there's a wing design that allows for both high speeds, maneuverability, and short take offs/landings. Like a swept wing... idk carbon cub? lol
If you have such a design you would be very rich!
You would need to have a wing that can change it's shape, with either flaps, slats, both, or something else entirely.
So is this why the f14 has a delta wing while wings are retracted
Anyone else studying for your A & P?
Where is the rest of the presentation?
www.pilottraining.ca
I was hoping that he would explain the sweptback wings of jet airliners but I still love the explanation👍
Real engineering has a video abou that
@@ryanbertelsen8880 I already watched that.
@@ChrisZoomER makes sense, it has been 6 months
Pretty much the only valid reason for wing sweep is to allow thicker wing sections to be flow at higher speeds than their critical Mach numbers for their respective thick-airfoil sections.
e.g. an Airfoil that is 14% thickness to chord (height to length) might have a critical Mach number of 0.68 (68% the speed of sound). And an 9% Airfoil might have a critical mach number of 0.85.
But a highly swept 14% thick Airfoil, which has more internal volume for structure and fuel, can attain the same Mach number speeds as a 9% Airfoil which has no sweep.
@@ChrisZoomER given this comment is 9 months old I think you might've watched that too, but there is also another video about forward swept wings, made by Real Engineering... and also one made by Millenium 7*
I always imagine I’m an aeronautical engineer 😂😂😂. Seriously, I just want an LSA with ultra low cost just to have my slice of nirvana.
'Hershey Bar' planform.
What does he mean by stall??
Stall refers to the wing losing lift/control. Typically due to low speed, high attack angle or both.
@@nxnickk thank you man
you mixed up delta and tapered............
no? delta is a triangle while tapered starts out rectangular then slopes but usually never comes to a point.
Must consider the economic aspects for leisure and commercial missions as well as the speed/altitude regime they will work on. Swept planforms and elliptical cost much more. Swept wings do not have good handling characteristics. Swept wings and swept tail feathers are actually worse performers at subsonic speeds under, say, Mach 0.6. For military applications, the price is of no consideration vs air superiority. Neither is the handling, unless you believe there will be dogfights in the future (highly unlikely, but possible)
I’m as stupid after, as I was before.
No explanation whatsoever of anything.
Why TF stop it there????
hershey bar lol, veryyy american
sir laminar is best
Why dont they design wings like a dart...
Fletching on arrows was developed in medieval times because it offered superior air control...
Because wings need to provide lift and support the entire weight of the aircraft while fletching on arrows is mainly just for stabilization.