This is awesome! Possibly THE best visualisation of laminar vs turbulent airflow above the wing in a stall situation I have ever seen anywhere. Thank you!
love the strings!! very clever, I can imagine the work it took to put them all in place too. Thank you for this greatly detailed video review before my CFI checkride next week!
Well now this is interesting, if I'm not mistaken Sporty's Pilot Shop is located about 20 min away from me at Clermont Co. airport here in OH. I'm going to be making a trip here soon to take the written test for my part 107 cert.
Best way to see a stall is with an aerofoil in a wind tunnel connected to a multiple manometer, with alternate manometers connected to alternate sides of the aerofoil. Lift is is roughly proportional to the area you can see delineated by manometer levels. At an angle of attack of 12-14 degrees you will see a sudden drop in area. This is the stall, and it is accompanied by a big increase in drag which should be avoided. In addition the flow is likely to change from steady flow to distinctly unsteady flow, and the pilot of an aeroplane will feel some buffeting after a stall. In an aerofoil on the point of stalling, vorticity diffuses out from the front of the aerofoil and should be reabsorbed at the back. This reabsorption is a precarious process for the almost-stalled aerofoil on the upper surface at the rear, and fails catastrophically once stalling has begun.
Hello, Do I understand it right that, Stall will happen when you have a large angle of attack at relative low speed? But if, with the Same Angle of Attack, the speed is much higher, then stall won't happen. Right? And the plane will climb up of course. Right? If right, What are those speeds and angle of attacks? If not right, Then how come that fighter jets and other acrobatic planes can climb strait vertically? I suppose this is because of their high speed, which provides enough lift, no matter in what direction they move. So why can't normal plans in a critical angle of attack give full throttle to gain more lift?
I think it's because angle of attack is not the same as pitch. The angle of attack is the difference between the pitch of the aircraft relative to the horizon and the flight path vector of the aircraft (which direction the aircraft is actually moving). If you're able to pitch up to 60 degrees but the aircraft is moving on a flight path vector of 55 degrees, I believe you only have an angle of attack of 5 degrees and so a stall is unlikely to occur. This is my understanding, but it may be beneficial for someone with better knowledge to respond to my answer. :)
Stall happens at the same angle of attack regardless of speed. The reason a stall is associated with low speed is because you would need a high angle of attack to maintain level flight at low speed. The slower you go, the more you have to pitch up the plane. Eventually you pitch it too far and it stalls.
@@sparky8729 Thanks for explaining this. But the fighter jets does not stalls when they pitch up at extreem angles. Why? I think it's only because of their high thrust. So that their flight path is the same as their pitch and nose. Stall happens when your flight path is not exactly the same as your pitch and direction of nose. That's why the angle of attack increases too much, and stall happens. Do I understand it right now?
No, lift isn't caused by low pressure above a wing. Lift is low pressure above a wing. Lift doesn't cause lift. Wings get lift by deflecting air. You dont get low pressure and then get lift from the low pressure. You get the pressure differential when you deflect air. If you don't, you don't get lift.
Not necessarily, wing foil can create the pressure difference with 0 angle of attack. They do it by creating vortex(not in a general scence) around the wing, instead of deflecting the air particles
The string thing is just beautiful for explaining stall.
This is awesome! Possibly THE best visualisation of laminar vs turbulent airflow above the wing in a stall situation I have ever seen anywhere. Thank you!
wdym i dont see anything that mentions laminar
@@maxweber1069 when the tufts are perfectly aligned the flow is laminar, when the tufts are getting crazy its a turbulent flow
love the strings!! very clever, I can imagine the work it took to put them all in place too. Thank you for this greatly detailed video review before my CFI checkride next week!
Love this visual! Really helps to SEE how a stall occurs. Thanks!
Very well explained, thanks for the video
Well now this is interesting, if I'm not mistaken Sporty's Pilot Shop is located about 20 min away from me at Clermont Co. airport here in OH. I'm going to be making a trip here soon to take the written test for my part 107 cert.
Thank you very much~ this video is phenomenal
Best way to see a stall is with an aerofoil in a wind tunnel connected to a multiple manometer, with alternate manometers connected to alternate sides of the aerofoil. Lift is is roughly proportional to the area you can see delineated by manometer levels. At an angle of attack of 12-14 degrees you will see a sudden drop in area. This is the stall, and it is accompanied by a big increase in drag which should be avoided. In addition the flow is likely to change from steady flow to distinctly unsteady flow, and the pilot of an aeroplane will feel some buffeting after a stall.
In an aerofoil on the point of stalling, vorticity diffuses out from the front of the aerofoil and should be reabsorbed at the back. This reabsorption is a precarious process for the almost-stalled aerofoil on the upper surface at the rear, and fails catastrophically once stalling has begun.
thanks a lot
Wings stall when they stop deflecting air.
nice !!!
Hello,
Do I understand it right that,
Stall will happen when you have a large angle of attack at relative low speed?
But if, with the Same Angle of Attack, the speed is much higher, then stall won't happen. Right? And the plane will climb up of course. Right?
If right, What are those speeds and angle of attacks?
If not right, Then how come that fighter jets and other acrobatic planes can climb strait vertically?
I suppose this is because of their high speed, which provides enough lift, no matter in what direction they move.
So why can't normal plans in a critical angle of attack give full throttle to gain more lift?
I think it's because angle of attack is not the same as pitch. The angle of attack is the difference between the pitch of the aircraft relative to the horizon and the flight path vector of the aircraft (which direction the aircraft is actually moving). If you're able to pitch up to 60 degrees but the aircraft is moving on a flight path vector of 55 degrees, I believe you only have an angle of attack of 5 degrees and so a stall is unlikely to occur. This is my understanding, but it may be beneficial for someone with better knowledge to respond to my answer. :)
cause fighter jets are pretty much a rocket with wings attached lmao... that's why they can just go ^
Wing always stall with the same angle of attack.
Stall happens at the same angle of attack regardless of speed. The reason a stall is associated with low speed is because you would need a high angle of attack to maintain level flight at low speed. The slower you go, the more you have to pitch up the plane. Eventually you pitch it too far and it stalls.
@@sparky8729
Thanks for explaining this.
But the fighter jets does not stalls when they pitch up at extreem angles. Why?
I think it's only because of their high thrust. So that their flight path is the same as their pitch and nose.
Stall happens when your flight path is not exactly the same as your pitch and direction of nose.
That's why the angle of attack increases too much, and stall happens.
Do I understand it right now?
Came from Nepal plane crash where the cause is supposed to be aerodynamic stall
it's good
i dont understand it
@@maxweber1069 go to hell then , are u a pilot brother ?????
Angle of attack? What are they attacking
the wind
ze germans
Ukraine
No, lift isn't caused by low pressure above a wing. Lift is low pressure above a wing. Lift doesn't cause lift. Wings get lift by deflecting air. You dont get low pressure and then get lift from the low pressure. You get the pressure differential when you deflect air. If you don't, you don't get lift.
Semantics is so important😎
Not necessarily, wing foil can create the pressure difference with 0 angle of attack. They do it by creating vortex(not in a general scence) around the wing, instead of deflecting the air particles