Wake turbulence from the generating aircraft can affect encountering aircraft due to the strength, duration, and direction of the vortices. Wake turbulence can impose rolling moments exceeding the roll-control authority of encountering aircraft, causing possible injury to occupants and damage to aircraft. Pilots should always be aware of the possibility of a wake turbulence encounter when flying through the wake of another aircraft, and adjust the flight path accordingly.
But as per the book of EASA 08 for B1 and B2 certification of page no. 32( in book it is 2.14) :--- additionally, there are three types of parasite drag: 1. Form drag. 2. Skin friction drag. 3. Interference drag. like i may be wrong let me know if am right . thank you .
The reason for the form drug is turbulent flow after the separation point. If you increase the angle of attack, the separation point will move forward and we will have more turbulent flow over the wing. More turbulent flow = more form drag. Conclusion: If the angle of attack increases parasite drag WILL INCREASE Thanks for the video.
Went though your videos .. thanks for for sharing them... however in the Induced Drag video, you might like to relook both at the explanation of induced drag as well as the methods of reducing it.. wing fences, VGs are not used to reducing Induced drag..
It may not seem directly that they prevent induced drag but they do that a role to play. Any device which is preventing potential stall is basically reducing drag. Vortex generators and wing fences keep the airflow in line and re energize the boundary layer and in some senses prevent span wise flow which are responsible for creating induced drag.
acdcording to lift formula: L=CL x 1/2ρv²S, if speed increase, lift will increase, if lift increases, induce drag will also increase, which means speed increases, induced drag increases. somthing wrong? (assuming wing area and CL is constant)
There is a difference. 1/2 ρ V² is IAS, where as V alone is TAS. So it depends what speed you plan to increase. If you are planning to increase TAS, it has to be compensated. where as IAS is automatically compensated with density. Also, You cannot keep constant parameters just like that, when you increase speed, You will indeed increase lift but till a certain point. CL is depended on camber and angle of attack. So you cannot increase lift indefinitely by keeping other parameters constant, you have to change the angle of attack or density. That is where the minute relationship exists within the possible flight envelope. Just don't get yourself confused and simply remember these points and note them down for reference. Induced drag is proportional to Lift Square. Induced drag is proportional to Load Factor. Induced drag is inversely proportional to IAS squared. Induced drag is inversely proportional to Aspect Ratio.
Mate İ just wanted to thank you for this video. We had a difficult lesson as you know: aerodynamics. İ think İ performed outstandingly well thanks to your videos. İ expect more videos. Thanks deeply.
Thanks for all the videos I just have a confusion with regards to the last point which states AOA will not affect Parasite Drag if we increase AOA " wouldn't this attitude be giving more more parasite surface ?? Just a confusion Thanks in advance
It was actually not so direct. First things first - Parasite drag is independent of lift generation whereas induced drag is dependent on lift generation. So when it mentions AoA will not affect parasite drag meant that it will affect induced drag more.
+Ishwar Vyas They are anti shock bodies which eventually help in decreasing drag as in they help in smoothening out the airflow. They help in partially reducing both induced drag at slow speeds when flaps are deployed and at transonic speeds act as anti shock bodies to prevent splitting up of airflow which produces parasitic drag.
thanks for sharing knowledge. but only input,result,effects, practical approach to handle the problem is being explained not the why(physics behind it)???.
Actually parasite drag is affected by the AOA( indirectly)
Because when you increase the AOA, the area is creating called parasite area.
Wake turbulence from the generating aircraft can affect encountering aircraft due to the strength, duration, and direction of the vortices. Wake turbulence can impose rolling moments exceeding the roll-control authority of encountering aircraft, causing possible injury to occupants and damage to aircraft. Pilots should always be aware of the possibility of a wake turbulence encounter when flying through the wake of another aircraft, and adjust the flight path accordingly.
This video is epic, really helped me with learning it!
But as per the book of EASA 08 for B1 and B2 certification of page no. 32( in book it is 2.14) :---
additionally, there are three types of parasite drag:
1. Form drag.
2. Skin friction drag.
3. Interference drag.
like i may be wrong let me know if am right . thank you .
You can use them like these also!
it's very helpful when u r studying all alone .thanks mate
You are welcome!
Nice explanation!!
Very methodical, this man explains with,,,intelligence
Thank you!
The reason for the form drug is turbulent flow after the separation point. If you increase the angle of attack, the separation point will move forward and we will have more turbulent flow over the wing. More turbulent flow = more form drag.
Conclusion: If the angle of attack increases parasite drag WILL INCREASE
Thanks for the video.
Btw the altitude will decrease because the density will be less. (less air molecules)
Went though your videos .. thanks for for sharing them... however in the Induced Drag video, you might like to relook both at the explanation of induced drag as well as the methods of reducing it.. wing fences, VGs are not used to reducing Induced drag..
It may not seem directly that they prevent induced drag but they do that a role to play. Any device which is preventing potential stall is basically reducing drag. Vortex generators and wing fences keep the airflow in line and re energize the boundary layer and in some senses prevent span wise flow which are responsible for creating induced drag.
acdcording to lift formula: L=CL x 1/2ρv²S, if speed increase, lift will increase, if lift increases, induce drag will also increase, which means speed increases, induced drag increases. somthing wrong? (assuming wing area and CL is constant)
There is a difference. 1/2 ρ V² is IAS, where as V alone is TAS. So it depends what speed you plan to increase. If you are planning to increase TAS, it has to be compensated. where as IAS is automatically compensated with density.
Also, You cannot keep constant parameters just like that, when you increase speed, You will indeed increase lift but till a certain point. CL is depended on camber and angle of attack. So you cannot increase lift indefinitely by keeping other parameters constant, you have to change the angle of attack or density. That is where the minute relationship exists within the possible flight envelope.
Just don't get yourself confused and simply remember these points and note them down for reference.
Induced drag is proportional to Lift Square.
Induced drag is proportional to Load Factor.
Induced drag is inversely proportional to IAS squared.
Induced drag is inversely proportional to Aspect Ratio.
Thank uu for the video .it's so nicely explained 😄😄. one doubt the Vmd is the green dot speed in airbus ?
Yes
@@poh thank you 😄sir
Awesome video dude. I have aerodynamics exam. I hope I'll pass it. If I do so it is because of you. I assume you chose the same path as me.
+Berkay Ergun You're welcome!
first of all thank you sir , kindly i ask i can you make a video about airlaw or other materials .
Coming up!
@@poh best regards sir
Correction: can you
Engine-wing joint is at the Pylon. Nacelle is engine casing and it is aerodynamic. Pylons create drag.
+Vishesh Raj Srivastava Pylons are also aerodynamic.
Yup. I meant comparatively. Also, point was that Engine-Wing joint is called Pylon not Nacelle.
Really helpful!!
Thanks a lot!
Mate İ just wanted to thank you for this video. We had a difficult lesson as you know: aerodynamics. İ think İ performed outstandingly well thanks to your videos. İ expect more videos. Thanks deeply.
And İ adviced you to all the pilot students İ know. Btw dont forget to enable monotisation
+Berkay Ergun Pleasure. You're welcome.
After Long Time are you a pilot
Yes
great work bro
Wing fences and vortex generator is interchanged in explanation .it's wrong...please check it up.
clearcut explanations
Thanks man you are great .... wish you can do similar vids for AGK please
Request noted.
Good stuff! Play back speed to x1.5....
Nice presentation and good effort for drag.
+Rashmi Ranjan Nayak Thank you!
Thanks a lot bro
Quite helpful., great job bro
+Muzakkir Khan Welcome :)
Thanks for all the videos
I just have a confusion with regards to the last point which states AOA will not affect Parasite Drag if we increase AOA " wouldn't this attitude be giving more more parasite surface ??
Just a confusion
Thanks in advance
It was actually not so direct. First things first - Parasite drag is independent of lift generation whereas induced drag is dependent on lift generation. So when it mentions AoA will not affect parasite drag meant that it will affect induced drag more.
plz can you do gnav i love YOUR VIDS AND HAVE SHARED AND SUBSCRIBED
+Majid Qureshi I have noted down your request, hope to do it soon. :)
the best!!!!!!! keep going.
very nice sir.
Thank you!
How do I know what's the aspect ratio??????
+IRrTRIANCLE 53 It is ratio of wingspan to mean chord of the aerofoil.
the aspect ratio is the span to the mean chord of an air foil ( wing )
Width/length of the air foil ! :)
Aspect ratio =(wing span) *(wing span) /wing area
Does Flap Track Fairings decrease the induce drag ??
+Ishwar Vyas They are anti shock bodies which eventually help in decreasing drag as in they help in smoothening out the airflow. They help in partially reducing both induced drag at slow speeds when flaps are deployed and at transonic speeds act as anti shock bodies to prevent splitting up of airflow which produces parasitic drag.
13:16 Interesting what is that symbol on your bracelet
😄😄 its a Swastik!
Good job. well done
+Caroline Ndambuki Thank you!
Glide ratio related video banaiye pls
subscribed :)
can you explain plz whats is the difference of skin friction drag and skin friction coefficient plz??
Drag is the force, the coefficient is constant value that is specific to a type of surface or material used.
hello brother why form drag is called pressure drag?
Because it causes big changes in pressure around the aircraft
thanks for sharing knowledge.
but only input,result,effects,
practical approach to handle the problem is being explained not the why(physics behind it)???.
+himanshu dwivedi What exactly do you want to know? I mean what physics about it?
Your Coefficient of induced drag formula is wrong. please do check.
Could you let me know what's the correct one please. Thanks.
it is (CL SQUARE) DIVIDED BY (Pi*e*AR)
As per oxford it is (CL^2) divided by (AR) only.
what is ias
Indicated Air Speed! :)
Nice
Thank you! :)
🙏😊