The funny thing is, i was confused by these theories all semester but fortunately i found your video, a five-minute clip literally saved my life. I’m gonna make it A 😭
When you introduce the 2 types of stabilities, it'd be nice to hear a short definition on the differences. (i.e. based on the time period that is analyzed. When talking about Static Stability, only the moment is investigated after the disturbance, while for Dynamic Stability the whole time period of the motion is carried out.) Also, I'd show examples for a statically stable, neutral and unstable response in each case. Hope you find it useful, pretty good elementary introduction in fact.
For lateral static stability, why does the downgoing wing increase in AoA? Isn't the chord in relation to the airflow the same regardless of the disturbance in roll?
Good video just remember that it is not a matter of only altitude change here. For example, neutral longitudinal static stability does not mean the aircraft will maintain altitude of whatever the disturbance was but rather angle of attack. Therefore the altitude will continue to change. Whereas negative means it will change exponentially, and positive means it will return to stability (again, not necessarily the original altitude).
@@perceptronsaber4479 Hi. Thanks for the message. I am not designing. I kite surfing using hydrofoils and have options of wing and stabilizers to use and also can change angle of attack with shims. I don’t do any designing myself, just a user. So sorry collaborating with me will not be helpful. Regards.
The tail is a vertical surface, so any disturbance in roll or yaw cause the tail's vertical area to move into the disturbance, causing an increase in the drag!
Very nice simple explanation but there is a mistake @ 4:20. When the wind hits the plane from right the nose will turn to the direction of the wind which is in this case right.Because the wind will hit the vertical stabiliser which is located in the back of the plane from the right which makes the nose of the plane to move to the right
This would be true if the aircraft is stationary. But if the aircraft is moving forward, if wind hits the aircraft, it will hit the nose of the aircraft initially which will cause the aircraft to yaw towards the left!
@@JxJAVIATION can you please make a video on spin stall, Its clear that spin stall occurs because of presence of yaw during a stall, but I am trying to find the effects of the fuselage on the rearward wing stall during the formation of spin
A correction to understand stability we consider the aerodynamic centre and not centre of pressure as AC does not change with change in lift and a fixed reference is considered for calculation purpose.
Sorry, but this is one of the poorest explanations of longitudinal and lateral stability I have seen. I notice some comments by students saying this has helped them. Please don't use the explanations given here in an exam. In particular find out for yourself what the neutral point is, and understand why the centre of gravity must be in front of the neutral point for positive longitudinal static stability. Also, note that it is not necessary for a tailplane to push down for positive longitudinal static stability. If it is big enough or far enough behind the wing, it can shift the neutral point well behind the CP of the wing, so that the centre of gravity can be behind the wing CP.
Well, the video is just a visual representation of the concept of different types of stabilities applied on an aircraft. Practically speaking, how far would you design the tail plane. In a normal aircraft design, the tail is majorly responsible for creating a downward force.
The tailplane must be used to produce downward force only if the CP of the wing is behind the CG. As you said, the CP moves as a function of angle of attack. The best way of explaining longitudinal static stability is to start with the neutral point (NP). There is a tail off neutral point, and a tail on neutral point. Starting with the tail off neutral point, it is the axis perpendicular to the plane of symmetry where there is no change in pitch moment with change of angle of attack. But wings have camber, so at zero lift, there is inevitable a nose-down pitching moment about the tail-off NP. If the CG is ahead of the NP, the lift will produce more nose-down pitching moment about the CG as the angle of attack is increased. Adding a tailplane shifts the NP aft, because the tailplane produces nose down pitch moment as the angle of attack increases and negative pitch moment as the angle of attack decreases. How far the tail-on NP is behind the tail-off NP is determined by the tailplane volume ratio (gatepathshala.com/pdf/download/conceptoftailvolumestosizehorizontalandverticaltails.pdf). With a high tailplane volume ratio, at low angles of attack, the tailplane is not unlikely to lift. I remember my own surprise when one of my colleagues in the Aerodynamis Office at Hawker Siddeley Aviation, Kingston, first pointed this out to me in the 1970's. (He was in the loads and stores section which was responsible for determining the range of aerodynamic loads on the aircraft structure, and the aircraft was the Hawk trainer; I was a Flight Dynamicist). @@JxJAVIATION
![fellow fellow - พรุ่งนี้ไม่มีใครรู้ feat. INK WARUNTORN [OFFICIAL MV]](http://i.ytimg.com/vi/QP6JyjYx_W0/mqdefault.jpg)
Finally someone made static stability understandable!! Thank you so much
Cool! There is a video on Dynamic Stability also if you are interested!
Thanks man! I have an aerodynamics exam in 4 days, and this really helped.
Welcome and All the Best! :)
I have one tomorrow
u failed ur last one?
@@sencegame8685 No this was my first try.
How was the exam?
The most beautiful teaching method I've ever seen. 👍👍👍
Wow, thank you!
The funny thing is, i was confused by these theories all semester but fortunately i found your video, a five-minute clip literally saved my life. I’m gonna make it A 😭
Thank you! Do check out my other videos as well! All the Best!
mantap la boss, great explanation about the aircraft stability
Thank you! Check out my other videos as well!
Best explanation I've seen well done, thank you Keep up the videos.
Thank You! & Welcome! Check out my other videos as well!
Great video. Think its the first time I really understood.
Thank you! That's great. Check out my other videos as well!
totally helpful vid, THANKS
Glad it helped!
Wow your explanation is the best one👍👍👍👍
Thank you so much :)
Thank you for the good explanation
You are welcome!
Loved this video! Very clear and articulate!
Glad it was helpful!
lateral stability cintrol by aileron @@JxJAVIATION
Hello from Indonesia. Very useful here, Keep The Spirit !
Hello & THANK YOU! Do Watch my other videos as well!
Hi
I am AUTOMATION Engineer, can we collaborate in our research, please?
@@perceptronsaber4479 Hello, Sure. Sorry For Late Reply.
My Email : qqqivanvvv@gmail.com
Great Explanation, Thx Sir !
Most welcome!
When you introduce the 2 types of stabilities, it'd be nice to hear a short definition on the differences. (i.e. based on the time period that is analyzed. When talking about Static Stability, only the moment is investigated after the disturbance, while for Dynamic Stability the whole time period of the motion is carried out.)
Also, I'd show examples for a statically stable, neutral and unstable response in each case.
Hope you find it useful, pretty good elementary introduction in fact.
Thank you for the feedback.
Creating a separate video for Dynamic Stability so I did not include that concept in this video.
It was so helpfull, thank you
Glad it was helpful!
Hi
I am AUTOMATION Engineer, can we collaborate in our research, please?
Awesome explanation thank you! Really helped me to understand 😀👍🏼🙏🏼
Glad it helped! Check out my other videos as well!
Thank you very much, keep posting.
Thank you too! Please Share and Watch my other videos as well
For lateral static stability, why does the downgoing wing increase in AoA? Isn't the chord in relation to the airflow the same regardless of the disturbance in roll?
If we look at the local airflow on the downgoing wing, it would seem like an increase in the AoA, which causes an increase in the lift.
your videos really helped me keep it up!
Glad to hear it!
Thanks a lot!!! Keep making more contents. Can you tell me which resources did you follow for Aircraft Stability?
Welcome! I used books by Clancy and JD Anderson and a few research papers
Thanks for your reply
At 3:50..didnt he reverse the angle of attack of both wings?
perfect and clear
Thank you! Check out my other video as well!
fantastic explanation. cheers!
Glad it was helpful! Cheers!
Nice Video! thank you
Welcome! Check out my other videos as well! :)
thank you very much, this helped me so much :)
You're welcome!
Good video
Thank you! Do check out my other videos as well!
Thanks alot mate, was very helpful.
Glad it helped :)
Hi
I am AUTOMATION Engineer, can we collaborate in our research, please?
Thank you 😊🙏
Thank you. Check out my other videos as well!
Thanks mate this was very helpful!
Glad it helped!:)
Amazing video!
Thank you!
Thanks for the video, help me a lot.
You are Welcome!
Hi
I am AUTOMATION Engineer, can we collaborate in our research, please?
This was very helpful thank you so much!!
Welcome mate!
really good video, thank you very much
Glad you liked it!
Good job keep up
Thank you
Thanks and welcome!
Good video just remember that it is not a matter of only altitude change here. For example, neutral longitudinal static stability does not mean the aircraft will maintain altitude of whatever the disturbance was but rather angle of attack. Therefore the altitude will continue to change. Whereas negative means it will change exponentially, and positive means it will return to stability (again, not necessarily the original altitude).
Thank you for the input! Do check out my other videos as well!
Nice Video! Good Job
Thanks! Check out my other videos as well!
Very helpful thank you so much. Was there a reason that you omitted dihedral angle for the lateral stability?
Made a separate video on dynamic stability, which is why I omitted it.
Hi. Thank you for making this video, very helpful in my learning of kite surf hydrofoils from wing and stabiliser design. Regards.
You are welcome!
Hi
I am AUTOMATION Engineer, can we collaborate in our research, please?
@@perceptronsaber4479 Hi. Thanks for the message. I am not designing. I kite surfing using hydrofoils and have options of wing and stabilizers to use and also can change angle of attack with shims. I don’t do any designing myself, just a user. So sorry collaborating with me will not be helpful. Regards.
@@irf888
You are welcome
nice Bro
Thanks! Check out my other videos as well!
Sir, How the lift increases in Downgoing wing in lateral stability as the aircraft rolls?
The downgoing wing experiences an increase in AoA because of this movement. This causes an increase in lift.
Thank u so much sir
Most welcome! Check out my other videos as well! :)
Thhank you
Welcome!
okay so there is an opposite reaction in the tail but why is there an increase in drag that makes it yaw back? many thanks in advance!
The tail is a vertical surface, so any disturbance in roll or yaw cause the tail's vertical area to move into the disturbance, causing an increase in the drag!
Very nice simple explanation but there is a mistake @ 4:20. When the wind hits the plane from right the nose will turn to the direction of the wind which is in this case right.Because the wind will hit the vertical stabiliser which is located in the back of the plane from the right which makes the nose of the plane to move to the right
This would be true if the aircraft is stationary. But if the aircraft is moving forward, if wind hits the aircraft, it will hit the nose of the aircraft initially which will cause the aircraft to yaw towards the left!
But all the kinds of static stability may be negative/neutral as well, right?
Yes has positive, negative and neutral
how does the horizontal stabalizer create a downward force
Opposite to what the wings do
It doesn’t yaw with the wind gust it yaws into the relative wind just like a weather vane does
Yes that is correct! The Weathercock effect!
Keep in mind that the aerodynamic forces are purposely put not on the center of pressure but the aerodynamic center or neutral point.
Yes! Thanks for clarifying!
Tanks 🙏🙏🙏
Welcome!
Lift increases on the down going wing ?
As the wing goes down it feels like an increase in Angle of Attack with the incoming air, which causes an increase in lift!
@@JxJAVIATION couldn't get it
@@JxJAVIATION it must be reverse I think
u need to go back to kindergarten to understand this
edit: great video, at 3:20 the horizontal stabilizer airfoil should be upside down as it provides a negative force. it's just a little confusing.
I think you are talking about the horizontal stabilizer. The image depicts the forces acting on the aircraft during straight and level flight.
@@JxJAVIATION can you please make a video on spin stall, Its clear that spin stall occurs because of presence of yaw during a stall, but I am trying to find the effects of the fuselage on the rearward wing stall during the formation of spin
@@BreakingMechs You could watch my video on Dynamic Stability where I discussed a little about it. But I will note down this topic for making video!
Sir ... Kindly upload one video about Anhedral and dihedral sir please...
noted!! Will try to create a video on this soon!
A correction to understand stability we consider the aerodynamic centre and not centre of pressure as AC does not change with change in lift and a fixed reference is considered for calculation purpose.
Hi
I am AUTOMATION Engineer, can we collaborate in our research, please?
I think it is the Aileron that helps the aircraft in lateral stability and not the Rudder
it is a combination of both!
I wonder if the 737 MAX designer watched this video?
Guess that person missed the video!
they knew that, thats why they had the MCAS.
so wing sweep has no effect on lateral stability??
wing sweep also has some contribution towards the directional stability
@@JxJAVIATION and dihedral/anhedral?? (BTW I know the answers)
@@davidinnes8754 I have made a separate video on dihedral and anhedral wings which you could watch.
Where are you from???
From India!
@@JxJAVIATION oh wow! keep making such informative and beautiful videos for us🥰🥰
@@pilot.sakshi That's the Plan! Check out some of my other videos as well!
Plzz provide pdf also
Well I didn't make a pdf for the topics
@@JxJAVIATION from next video plzz provide for that will help in our semester exam plzzzzz
Nowadays you can achive stability by means other than mechanical design
The basic mechanical design is available on all the aircraft. Modifications are done on it to improve the aircraft stability
@@JxJAVIATION There have been some aircraft which are not stable per mechanical design .
@@davidinnes8754 these would be aircraft that are required to perform severe maneuvers.
we know what stabilizers do.. we want to know how they do...🧐
I have uploaded a video on Trimmable Horizontal Stabilizer which could be useful for you!
@@JxJAVIATION ❤❤🤝
Tim has an Indian accent :D
Haha! Guess he does!
So. An increase in altitude will cause either of the 3 forms of stability to decrease - however spiral stability will increase.
The aircraft design has a direct impact on the stability!
Can’t understand
Teddy
Sorry, but this is one of the poorest explanations of longitudinal and lateral stability I have seen. I notice some comments by students saying this has helped them. Please don't use the explanations given here in an exam. In particular find out for yourself what the neutral point is, and understand why the centre of gravity must be in front of the neutral point for positive longitudinal static stability. Also, note that it is not necessary for a tailplane to push down for positive longitudinal static stability. If it is big enough or far enough behind the wing, it can shift the neutral point well behind the CP of the wing, so that the centre of gravity can be behind the wing CP.
Well, the video is just a visual representation of the concept of different types of stabilities applied on an aircraft. Practically speaking, how far would you design the tail plane. In a normal aircraft design, the tail is majorly responsible for creating a downward force.
The tailplane must be used to produce downward force only if the CP of the wing is behind the CG. As you said, the CP moves as a function of angle of attack. The best way of explaining longitudinal static stability is to start with the neutral point (NP). There is a tail off neutral point, and a tail on neutral point. Starting with the tail off neutral point, it is the axis perpendicular to the plane of symmetry where there is no change in pitch moment with change of angle of attack. But wings have camber, so at zero lift, there is inevitable a nose-down pitching moment about the tail-off NP. If the CG is ahead of the NP, the lift will produce more nose-down pitching moment about the CG as the angle of attack is increased. Adding a tailplane shifts the NP aft, because the tailplane produces nose down pitch moment as the angle of attack increases and negative pitch moment as the angle of attack decreases. How far the tail-on NP is behind the tail-off NP is determined by the tailplane volume ratio (gatepathshala.com/pdf/download/conceptoftailvolumestosizehorizontalandverticaltails.pdf). With a high tailplane volume ratio, at low angles of attack, the tailplane is not unlikely to lift. I remember my own surprise when one of my colleagues in the Aerodynamis Office at Hawker Siddeley Aviation, Kingston, first pointed this out to me in the 1970's. (He was in the loads and stores section which was responsible for determining the range of aerodynamic loads on the aircraft structure, and the aircraft was the Hawk trainer; I was a Flight Dynamicist). @@JxJAVIATION
You do not understand aerodynamics. You should delete or correct this video after you properly study and understand aerodynamics.
I do a lot of research before creating the videos. Perhaps you could explain what is incorrect in this video instead of posting such statements!
Bad pronunciation of words
Apologies for that!
you are just confusiong
Please explain!
Awesome explanation. Thanks.
You are welcome!