How to calculate lift? Lift coefficient and angle of attack.
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- Опубликовано: 14 июл 2024
- Hi guys! Welcome to another lesson in the "Introduction to Aerodynamics" series!
In this video we will talk about the formula that we use to calculate the value of the lift force on the aircraft. Also, we talk about the lift coefficient and how it depends on the angle of attack.
Let me know what you think of the video in the comments and subscribe to my channel to stay tuned!
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Thank you so much, your content is so precious to me! I am a computer science student and flying planes is a hobby for me! I wanted to make it more professional to me so I was looking for someone who explain aerodynamics "things" from the ground. Thabk you so much!⚘
Beautifully explained! Thank you very much!!
Thankyou !! You have explained a major topic in a very simple and understandable manner this is the best video to understand the importance of Cl and Cd
You explain the concepts so clearly at a comfortable pace!! I needed a review of the knowledge and your videos were amazing. Thank you so much!!
Thank you so much! Glad you found them helpful!
Thank you mam . you explain so clearly.
Very clear . Good video !
Thank you so much for this video... its very useful..!!
Perfect, thanks!
These videos are very helpful. ❤Thank you, ma'am. Kindly post many videos on propulsion and aerodynamics, looking forward....
Excellent!
hi aliya. Thank you for your videos. I am currently doing a report on a wind tunnel test and youre videos have helped me to get an idea of what im doing. Online learning is very difficult and my university prof isnt that great. I appreciate your help!
Glad you found it helpful! Thank you for watching! Good luck with your report!
Thank you so much 🥰🥰 great job
So Nice explanation 😊
Hi thanks for explanations
Please consider making explanation of moment coefficients (pitch,yaw,roll)
Symmetric! ;D
exactly!
i want to learn aerospace engineering from you . Really love how you explain clearly and easily to us. Waiting for future vedios to learn more
thank you so much!
@@AliyaBurkit yes ! the best explanations yet !
Great 👍
You are a life saver thank you
You're welcome
Nice explain 🔥
You are awesome!
Thank you for this amazing tutorial. You make learning so much easier, fun and interesting!
When is the next video coming up?
Very soon!
love ur explanations from sri lanka we are waiting for your more videos please continue teacher you are an awesome teacher as well as your so much beautiful
Yes, I will come back 😅
Excellent! Tell about briefly for coefficient momentum of airfoil
Excellent, great content!
Much appreciated!
Im from INDIA. You are very awesome and nice explanation.. your video is very helpful for me to calculating the lift of my own helicopter..
💀💀💀💀
Thanks!! :)
Great !!!
Thanks!
Keep it up Aliya!
Thanks! I will 😊
allways to the sharp point, I am very pround of HUMANITY .
Hi Aliya, I watched your video with keen interest. It unraveled some of my misconceptions.
Can you kindly explain the effect of Suction Pressure on Lift and Drag.
Thanks.
hey aliya could you please make a video explaining pitching moment specifically regarding the Cm = Cmo - hCl equation, moment at zero lift and aero center. Thanks!
You explain very well. It is better you also write down what is S, q, L, D (on the screen as well). That would make it easier to understand for the viewers.
prisitine!
amazing lady... amazing initiative
Thank you so much!
Nice...Waiting for your next Upload... :-)
Thanks!
Thank you very much for this video. It helps with Pilot training. Are you a pilot as well?
i use xflr5 and im doing airfoils analysis and looking their cl-alpha graphic. I can read airfoils clmax but How do I determine the clmax required for my plane?
best lift video yet
symmetrical airfoil should be 0 Cl at 0 AoA. Benefit is center of pressure doesn't move at dif AoA, unlike asymmetrical airfoils where cop shifts forward
Thanks, haha
Yes
May i ask you a question , how do i calculate parasite drag and Oswald effective factor ?
You're amazing! :)
Thanks :)
PLease if possible also do a video on ejection seats in fighter jet
Very great video. How many RPM to fly the helicopter?
Hey, can Cl for an aircraft wing be less than 0.3 for an Rc aircraft which is capable of lifting 6Kg payload
Im actually a student taking part in the SAE Aero competition and we are currently doing the calculations of cl and cd using numerical values. We used weight instead of lift in the cl formula to get values of cl but we are stuck in the cd part as they are no alternative formulas to find cd and Drag. So can u pls guide us on this
Nice explanation! Thank you for make it easier to understand Aliya. By the way is there any equation or formula to obtain the angle of attack correspond to the Cl and Cd without doing the test in Wind Tunnel?
Thank you
Good question! I will try to make a video about it (but much later)
can you help me with this...
A moderate speed aircraft moving at a speed of 13 ms-1 whose wing span
and aspect ratio is 150 cm and 5 respectively. Assuming suitable wing
loading and density of air calculate the lift generated by the wing at cruise
speed.
[Take g = 10 m/s2].
Mam your voice is sooo sweet
I have made Airfoil 4412 of chord length 152.4mm what will be the surface are of that which will be used to calculate Coefficent of Lift? , Please Answer
We have made a propeller and is it possible to determine the lift and drag coefficient through experiments? How can we carry out experiments?
how do you calculate Cl using air speed for example at yo ktas q is 48.6 I'm using the M20 airfoil how can I find my CL specific to the speed?
Hi Aliya!! Will you in the next video mention control systems in Aerospace engineering?
Hi Almaz, no, not yet. I will make videos on that topic last 😅
a symmetrical one 7:56
Mam can you please make a video on Cp distribution on wing surface
If I’m not wrong the CL at zero is a symmetrical airfoil as it doesn’t create and change in pressure therefore no lift
9:57 Meanwhile in Ace Combat 7 everyone does post-stall manuevers inside tunnels and stadiums!? ('o')
"trigger's different"
Is it the flat airfoil (plate)?
Hi, I have the lift coefficient and drag coefficient versus alpha curves , how can i find lift and drag through it as the curves gives a range of values , so what value of cl and cd should we take to find lift and drag?
Good question! It depends at which angle of attack the aircraft is flying (so for which alpha you want to find lift). Then you find that intersection of alpha value and CL or CD
Hi ,please can you tell me what the lift coefficient is, if the angle of attack 2 for NACA 65-210. I studied a graphy about this topic but Frankly I cannot understand the grafic.
But can we write the lifting force as: (cLmax×sin(alpha/2))?
When angle of attack>critical angle, why will there be no lift near the trailing edge, air flow below the airfoil is still attached. Wouldn't that increase the lift?
So, what will the Cl and Cd of NACA0018 at angle 45, 90, 135, 180, 225, 270, 315, 360
can you plz let me know cuz I couldn't able to find this on any sort of platform. can you plz help me with that!!!!!
I am confused - what happens if the aircraft has a lot of thrust like a jet... it won't stall if a high AOA is reached. But it would stall if there is not enough thrust. Isn't thrust an important part of the equation?
so if i understand correctly there is no single equation to derive the correlation between coefficient of lift and angle of attack, its derived from a lot of experiments done on the wing right?
symmetric airfoil (NACA 0012......)has Cl=0 at 0 degrees of angle of attack , Symmetric airfoil use for 3D fly helicopter ;)
How about the velocity of the air flow on helicopter blade when it rotate? there are a lot of difference speed of the air belong the heli blade because it rotate on the blade shaft. the position nearer the shaft have lower speed , the position nearer the tip of the blade have higher speed ! Please tell me how can i calculate the lift or drag of the helicopter blade. thk you very much !
Symmetric airfoils !!
How to calculate lift for wing plate?
In your other video, you say that lift coefficient is a function of (Angle of attack, Mach number and Reynolds number) But in the formula mentioned in this video, these variables are not mentioned?
how to determine the correct lift coefficient with angle of attack(10 degrees), when it gives three graphs with each one's Re is 50000, 200000 and 500000. Please explain.
So how do you work out the coefficient without a wind tunnel.
Trial and error 😂 in the field
You remind me of MY A-LEVEL MATHS TEACHER MR. SUNAK; I always think HE IS YOUR GRANDFATHER.
Haha I taught A-level at some point
what is the formula in order to calculate lift coefficient ? NACA files do not tell you the way of getting LC and DC. Only tell max cumber:locations of MC And max thickness. How do I get LC. Thanks
Good question. I guess I need to make another video about this topic
Symmetrical airfoil
symetrical airfoil?
i do not have wind tunnel
Hi, I have a question. Is drag force usually greater than lift force at a given speed?
6:20
The amount of drag (and therefore thrust) force is always smaller than the lift (and therefore weight) force.
I love you mam for good teaching.
Reply me.
Thank you for watching!
@@AliyaBurkit mm
@@AliyaBurkit I am new subscriber .
@@AliyaBurkit I am studying ame I want clear explanation of co efficient lift.
Thanks for joining!
Why do you say that we have to look for the lift coeff of the wing? Let say that the lift equal weight then you replace the number of the lift force by the weight of the aircraft in newton and if you know the surface of the wing and the speed, you will find the lift coeff...am i wrong ?
symmetrical airfoil
Can you make a video about stall
Yes I will
@@AliyaBurkit Thank You 😋
Maybe sphere would have a lift of 0 at any angle of attack if the sphere is not spinning.
i want to learn aeromatical engineering mam
Great!
it would be perfect if you give true calculation with numbers and ansers such as for example how to find the Alfa degry for stall with numbers lets say s=1.6 m^2 v=30m/s and ect.....
Symmatrical AirFoil
True
Aliya please make your vids little bit longer like 40 min or so.
They are easy to learn and it seems like just a minute while watching.
Thanks so much! That's the goal 😊
@@AliyaBurkit Hey can you suggest which basic skills or knowledge like coding or calculus; and so on for studying aeronautics engineering. It would be really helpful. Lots Of Love(LOL). 😎🤷♀️🤷♀️💖😊 Sorry for bad english; hope you understand.
Sure
Im a 14 yo wanting to make a airplane simulator, thank you!
Sounds great! You would need to know coding well
@@AliyaBurkit I can use C# a bit, still learning but now I am using scratch
@@AliyaBurkit I got it yay
Yeah but i think that you are wrong because the Drag and lift coeficients of an airfoil have different values from the drag and lift coeficients of a wing. Am i wrong ?
Answer to the question is --" Symmetric Airfoil "
young lady, you must be ruling NASA, such clarity on concepts and easiness explaining them,...you will horrorized , to see aerospace engeeners tring to explain the same......a really saad story....
İf we no have lift , we have just angle of attack, how calculate lift coefficient? Can you tell me please?
You mean when the angle of attack is too large and we don't have lift anymore? It's called critical angle of attack, you can find it from the table of the airfoil
I got it, Thank you.
What is wind tunnel?
good question)) I guess I need to explain it in a separate video
I AM HERE TO LEARN. BUT WHY AM I SIMPING ALL OF A SUDDEN
??
An aircraft is flying at an altitude of 15000ft at a temperature of -39 degrees Fahrenheit. If the wing chord is 6ft, its wingspan is 45ft and the equivalent speed is 200ks.
1) Determine the lift force generated with the following data, for a 4 degree angle.
Mam i want the answer plz reply me mam it's urgent now
It would be helpful, (crucial) to know the aerofoil section, and /or CL for the wing section in question, and also the CL vs Alpha (angle of attack) chart of that section.
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).
I think a flat airfoil would have a zero angle of attack
You mean zero lift?
A flat airfoil could still have an angle of attack
@@AliyaBurkit Angle of attack is created by moving airfoil upward .In that case every airfoil has an angle of attack .Besides no lift is available without it .If so how a zero angle of attack possible ?
zero angle of attack is just parallel to the ground
I’m enjoying your videos, but occasionally wince when you make a comment such as the stalled condition of a wing is dangerous. This could be simply a language difference, but it implies a judgement about the condition, and would be a very un-engineering like evaluation. A stalled condition is neither safe nor dangerous, but may be desirable or undesirable depending on other factors. A stall may be used to great advantage when lift is not important but maneuvering is. To an engineer, a glass is neither half empty nor half full, but simply filled to 50% of its available volume. :)
I would also point out that while many advanced aircraft may be limited to an envelope that avoids a stalled condition through software parameters, there are many other non computer magic ways to try to accomplish the same thing. Pitch authority may be limited by elevator design, stall resistant airfoils may be chosen, or aircraft configuration with canard designs will all provide margins.
Thanks for the videos as I said I’m enjoying them.
True, thank you for pointing that out
Symmetric airfoil
Yes