The Basics of Aerodynamics
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- เผยแพร่เมื่อ 9 มิ.ย. 2024
- This is a short tutorial on the basics of aerodynamics, which explains some basic concepts of how airplanes fly. It was developed using Powerpoint drawing tools and recorded using Camtasia 2 for Mac.
Thanks for your video as an aspiring pilot TH-cam has been my main teacher I look forward to learning more from your videos keep up the hard work
1:55 if you listen carefully you can hear him flipping the page in the background xD,
btw thanks bro, awesome video
Hi, I am a practicing Aerospace/Aeronautical Engineer.
With due respect to you, I found that your presentation can be better if you pay more attention to basic Aerodynamic facts.
Firstly, the concept of fluids traveling faster does mean nothing to science; its a result of energy balance as per Bernoulli.
Secondly, Relative Wind is not a force, it is in fact a cause of various Aerodynamic forces on the Airfoil. Relative wind can be best explained by the Relative wind velocity.
Airfoil is not "a surface such as a wing"; it is at best a cross -section; remember we can have both Two-dimensional and also 3 dimensional airfoils.
The airflow velocity on the upper surface depends on various factors like up wash, camber,angle of attack etc.
When you talk of the circulation you must describe in detail what you mean.
The flow leaving at the down wash is one of the main causes of lift.
Your definition of Camber is also not correct. Camber is the asymmetry between the upper and lower surfaces.
Also, chord line is basically the shortest distance (straight line)between the Leading and trailing edges of the Airfoil.
The stall is not a result of the Critical Angle of attack; in fact we get the max. coefficient of lift corresponding to the Critical angle of attack, beyond which due to progressive separation of air on the upper surface that moves towards the leading edge,along with increased surface drag, we get total loss of lift creating the Stalling condition.In fact if the flow separation occurred just at the trailing edge as you explain, it would have been a very desirable effect!
Lastly, as XPLAIN has correctly mentioned, a complete equilibrium can be possible only when the Lift = Weight and the Thrust=Drag condition.
Good Luck!
Partha Sinha could u explain why its important for the air to flow smoothly above the wing? Im guessing it has to do with the 3rd newton law?
Whoa even I want to become an aeronautical engineer
correct
Good video! Highly Recommend to get A Better Microphone.
This video is wrong in many respects. I am not a student pilot but I am a career pilot and engineer. To start with the explanation of Bernoulli’s theorem is wrong. The fluid does not speed up “to reach the end of the curve”. This explains nothing. The fluid does not make a decision to go faster to reach the end of a curve. The velocity increases due to the physical constraint of the conservation laws. In order for momentum to be conserved the velocity has to increase in order maintain the mass flow rate. You can also explain the Bernoulli effect in terms of conservation of pressure energy. Because the fluid velocity increased the kinetic energy of the fluid increased. The increased kinetic energy of the molecules can be seen as a redirection of the pressure energy hence the fluid has increased dynamic pressure at the expense of reduced static pressure. If you want to reduce the explanation to simple statements such as the “fluid speeds up to reach the end of the curve’ you have not simplified the explanation, you have simply made it wrong.
Next we have a very poor description of the stall. A wing stalls at its critical angle of attack yes. But the stall is not “the result of a critical angle of attack”. The critical angle of attack is defined as the point at which the wing stalls, so if anything the critical angle of attack results from the inherent individual stall property of any given airfoil. However once the critical angle of attack is known you can say the wing will always stall when it reaches the critical angle of attack. Also you say that in a stall the airflow “separates at the trailing edge”. This is completely false. In a stall the airflow separates well before reaching the trailing edge. That is one of the key points to know. The lift depends upon the streamlines staying attached for as long as possible as the angle of attack is increased. The early separation of the streamlines and resultant increased turbulent wake are the two things that give the loss of lift and increased drag associated with the stall. If you could keep the upper flow attached all the way to the trailing edge, the wing would not be stalled.
Also, you say that an aircraft is in a state of equilibrium if the lift equals the weight. However, the aircraft can only be in a state of equilibrium if lift equals weight AND thrust equals drag. Otherwise the aircraft will be accelerating or decelerating and therefore the lift will be changing.
Finally you show two vectors and a resultant by way of explaining “the resultant of two opposing forces which are equal in magnitude is zero”. And yet the two vectors in the diagram are not opposing each other, hence they have a non-zero resultant. The correct explanation would be that the aircraft would be in equilibrium when the resultant of the thrust and weight vectors is equal and opposite to the resultant of the lift and drag vectors.
Geez, a kind of complicated way to explain something pretty simple, that the wing is moving thru the airmass and the top is longer than the bottom. Visualize what would happen if the air on top did not speed up. What would be the end result? Btw, good joke. Air is an inanimate object. It cannot make a decision. Sometimes an education is worse than no education at all. There is not a thing wrong with saying "it speeds up to reach the end of the curve". Also, btw, simple AoA is by far the main factor causing lift of a wing, not Bernouli
Who also has to study during Covid-19.Anybody.
Me but i'm no aerodynamics student lol.
I actually am just an artist giving a look at this kind of basics to design a spaceship.
I love having an excuse to stay home spending time doing theese silly yet interesting things c:
Uh im just experimenting with paper airplanes and wanna know more
I’m watching because I have a exam tomorrow . Lol
i just want to know what it means to understand the aerodynamics of a cow lol
yep
thank you for sharing your informations.
Thanks for this cool class brother.... ready for the next video
How would such a wing fly upside down? A stall is normally caused by the collapse of the shock wave above the wing.
Incorrect definition of chord line. It is a" line joining the leading and trailing edge of a wing."
its not wing....its airfoil
@@thesinghmonu The airfoil is just a 2D wing so it's correct
laucnhing a missile. very helpful 👍👍
Can you explain the difference between Angle of Incidence and Angle of Attack.
It is written in text book that Angle of Incidence (AOI) is a fixed geometry (between chord line and horizantal Aircraft axis) where as Angle of Attack (AOA) is variable as you have explained in the video
Please clarify
I'm quite late and you most likely figured it out but if anyone else will want to know, AoI is just what you said and AoA depends on the relative air hitting the airfoil, so even if a plane is facing 10 degrees up from the horizon the AoA could still be 0 degrees as long as the plane has enough airspeed to produce the lift equal to weight.
Fellas, chord line is the imaginary line from the leading edge to the trailing edge.
Angle of attack is the angle between the chord line and the relative wind.
Not quite. The chord line that matters is the one that bisects the lower and upper sufaces of the wing at its trailing edge. That is the direction that the airstream has to leave the wing, that direction is what determines the angle of attack.
When a plane is doing what is called "a knife edge" what keeps the plane from losing lift?
When an aircraft is doing an knife edge, the wing and the elevator or horizontal stabiliser are not producing lift at all and they are merely redundant assuming that the body of the plane will keep going straight.
The lift to keep the plane up is produced by the side area of the fuselage, which is kept at the right angle of attack by the rudder or vertical stabilizer now acting to control the horizontal angle of attack of the fuselage. At this angle with a large side are one side of the fuselage suffers a compression and while the air escapes as it does on wing tips the escaping air will produce some partial vacuum on the other side which helps to produce enough lift. But with such a high angle of attack on the side of the plane, the nose of the engine is high and the vertical thrust component from the engine will add a substantial amount of lift, so the lift from the fuselage side is not ad great as one expects and normally those aircraft which can do a knife edge are very high powered.
With a bit of imagination one can say that a bullet or a rocket fly in a knife edge state, With a bullet without a stabiliser at the back it is difficult, and a rocket with a stabiliser at the back it is easier. Well an expert who did know about all this is Robin Hood as all his arrows were not much different from unpowered knife edge travelling bodies in flight.
well the plane must have a thrust to weight ratio greater than 1
+JABd,
No. As Carmel says, the plane flys in an extreme nose up attitude.
The fuselage provides lift due to its high angle of attack and the engine has a larger vertical thrust component aiding the fuselage lift.
Lift force by fuselage and fin/rudder plus vertical thrust component
Nice thanks for making a video that is easy to understand
Very nice! I like it!
Excellent!
Its important to remember that low pressure above a wing doesn't cause lift, but rather is lift. For lift to occur, air must be deflected in a downwash. Downwash is the action while lift or pressure differential is the reaction. You don't get lift by creating low pressure. This would be like saying, lift causes lift. You only get lift by deflecting air. The bernuli
This video is underrated, sadly in the TH-cam world the more educational the content the lesser the viewers.
ye and it is quite good... besiedes the fact that the microphone was actual earrape
The lift created by a wing is created mainly by the down wash of air at the trailing edge of the wing. The low pressure above the wing only occurs right after the stagnation point at the leading edge of the wing. Using Bernoulli's principle to explain lift is not very accurate.
This does not seem quite right. This downwash leaves the trailing edge at the back of the wing. It does not act on the wing
What is the maximum angle of attack????
For many common wings it is about 15-16 degrees.
If you mean the critical angle of attack, about 16deg for most general aviation planes. But the angle of attack can be very much larger. The plane can pretty much fall down belly first e.g. in a flat spin. This would be close to 90deg angle of attack. Stalling does not equal loss of all lift.
Thank you sir
Great helped me keep it up
Thanks your videos and free engineering aerospace I am understand mechanical i need exam both avionics and mechanic this good preparation
Boy! Are YOU in trouble!
Would you upload a vedio that includes all terms that an aeronautical engineer should know
Why not?
Oh wait i misread
Sorry
Thank you bro
Please upload more videos of aerodynamics
how the maximum lift
Good video
i like the vid
🙏🏽
thanks to u
Simple air deflection, case closed.
More informations here: www.studyflight.com
More videos pls
Bernoulli is a crock! Explain how a flat airfoil flies.
A flat, or symmetric airfoil, generates lift through a positive angle of incidence. That's how aerobatic aircraft fly. When the angle of attack is 0 degrees, a symmetric airfoil generates no lift. However, add a slight positive angle of attack, and the symmetric airfoil flies.
+Sunayan Mullick,
ALL WINGS whether flat, cambered or inverted create lift at a positive *effective* angle of attack.
...
The angle of "incidence" is the angle of the wing mounted to the fuselage.
Observ45er And that is what I meant. You could get lift by attaching the wings to the fuselage at a positive angle of incidence. And yes, you’re gonna get lift as long as your effective angle of attack is positive.
+Sunayan Mullick,
Wings *are* mounted at some angle of incidence so the wing has a positive AoA and the fuselage is pretty much neutral during normal flight.
+Edward Brown,
Yes. Most other common explanations of Bernoulli's Principle are incorrect.
i'm just trying to build a plane in besiege.
DILG motorcycle barrier design brought me here -_-
The resultant of 2 equal perpendicular forces is not 0. Lol
I missed that one. You should have put the time.
The authors have two wrong scientific approaches: researching the creation of Lift force and Low pressure at upper side of the wing, relative to the ground surface and Earth. I explain the aerodynamic cavitation and existence of Lee side aerocavern, and creation of Aerodynamic force. Low pressure creates force normal to the cord (contact surface), and it name is "aerodynamic force" because is made from the air (aero) in motion (dynamic), or wind relative to the wing (object).
Im a kid just here to learn how to make a cool plane
There is no airfoil that looks like that.
CAN TAKA PLALIST
who also got an exam on this this month???
Poor video. lift force due to pre drop is not clear
This video adds nothing to the many other poor lift videos.
You need to follow the script correctly.
- The chord line is not drawn through the direction of the relative wind.
- Circulation is a method important for CALCULATING the lift force, but explains nothing.
- Your chord like is drawn incorrectly.
- The decreased pressure above a wing is the *cause* for the accelerated air.
- It also does not "Reduce the pressure drop".
- In stall, the air SEPARATION POINT progresses forward (not the air).
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Why is it called angle of attack when it should be called angle of the lift. That word should not even be used in aviation, I'm sweating over here
He doesn’t know anything about aerodynamics, he’s just reading off a book. Anyone can do that.
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i have to study
Why am I here
I have an aerospace engineering degree and I'm asking the same question! I don't have the answer
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Covid 19
Wrong.
Recently the 100yr opd Mystery of Airfoil Lift has been solved ! Check Tekemon.
The reason it took so long to get to the reality of lift was the basic error in assuming there’s some kind of flow of air over the airfoil, which gave rise to various erroneous non-existent and irrelevant concepts e.g. Bernoulli, Flow-Separation,etc. Everything is covered in the book, in detail. The matter was a very simple one, but the wind tunnel gave the scientists true tunnel vision for the past century. Check tekemon.
This video adds nothing to the many other poor lift videos.
You need to follow the script correctly.
- The chord line is not drawn through the direction of the relative wind.
- Circulation is a method important for CALCULATING the lift force, but explains nothing.
- Your chord like is drawn incorrectly.
- The decreased pressure above a wing is the cause for the accelerated air.
- It also does not "Reduce the pressure drop".
- In stall, the air SEPARATION POINT progresses forward (not the air).