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!!
@AliyaBurkit3 жыл бұрын
Thank you so much! Glad you found them helpful!
@omareldanasoury45973 жыл бұрын
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!⚘
@Fiendnat1383 жыл бұрын
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!
@AliyaBurkit3 жыл бұрын
Glad you found it helpful! Thank you for watching! Good luck with your report!
@LovepreetSingh-yt1qd6 ай бұрын
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
@mitalikoley51134 жыл бұрын
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
@AliyaBurkit4 жыл бұрын
thank you so much!
@HaritTrivedi73 жыл бұрын
@@AliyaBurkit yes ! the best explanations yet !
@vinothrouger2 жыл бұрын
These videos are very helpful. ❤Thank you, ma'am. Kindly post many videos on propulsion and aerodynamics, looking forward....
@ajaytechhyperloop21382 жыл бұрын
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..
@peggandwhiskey4 ай бұрын
💀💀💀💀
@ronaksamani28074 жыл бұрын
Symmetric! ;D
@AliyaBurkit4 жыл бұрын
exactly!
@_boss_mafia_3 жыл бұрын
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
@AliyaBurkit3 жыл бұрын
Yes, I will come back 😅
@engineersstuck.2 жыл бұрын
Thank you mam . you explain so clearly.
@claramelb74764 жыл бұрын
Thank you for this amazing tutorial. You make learning so much easier, fun and interesting! When is the next video coming up?
@AliyaBurkit4 жыл бұрын
Very soon!
@jhalakdhakal15962 жыл бұрын
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.
@Joao-hr3dkАй бұрын
So beautiful! 😮
@gopalkrishnamukerjea4319Ай бұрын
Excellent!
@kubilaykaan57443 жыл бұрын
You are a life saver thank you
@AliyaBurkit3 жыл бұрын
You're welcome
@snijdertkswr3 жыл бұрын
Hi thanks for explanations Please consider making explanation of moment coefficients (pitch,yaw,roll)
@pappafritto2 ай бұрын
Perfect, thanks!
@user-kr8wh6tr5n Жыл бұрын
Thank you very much for this video. It helps with Pilot training. Are you a pilot as well?
@GaiaKnight113 жыл бұрын
Beautifully explained! Thank you very much!!
@aliyusuleiman5287 Жыл бұрын
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.
@santhoshrohit042 жыл бұрын
Thank you so much for this video... its very useful..!!
@ajinharidhas59312 жыл бұрын
Excellent! Tell about briefly for coefficient momentum of airfoil
@anujregmi45824 жыл бұрын
amazing lady... amazing initiative
@AliyaBurkit4 жыл бұрын
Thank you so much!
@shadracknjane26783 жыл бұрын
allways to the sharp point, I am very pround of HUMANITY .
@e7zb4273 жыл бұрын
best lift video yet
@e7zb4273 жыл бұрын
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
@AliyaBurkit3 жыл бұрын
Thanks, haha
@AliyaBurkit3 жыл бұрын
Yes
@raghuvaran34172 жыл бұрын
Thank you so much 🥰🥰 great job
@dino11674 жыл бұрын
Nice...Waiting for your next Upload... :-)
@AliyaBurkit4 жыл бұрын
Thanks!
@isaacbongweiyik54723 жыл бұрын
Very clear . Good video !
@carlosmauriciovargasmachad43584 жыл бұрын
Excellent, great content!
@AliyaBurkit4 жыл бұрын
Much appreciated!
@farazhussain5279 Жыл бұрын
So Nice explanation 😊
@zainecooke9815 Жыл бұрын
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
@antoniofreitas53793 жыл бұрын
Very great video. How many RPM to fly the helicopter?
@makantahi373117 күн бұрын
nice: if an aircraft in a turn can continuously maintain a 5G load, what should be done for that same aircraft to achieve the same lift (which compensated for five times the force of weight) in a straight line climb, i.e. that while climbing it has 5 times more lift than the force of weight
@rahmatulputri49974 жыл бұрын
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
@AliyaBurkit4 жыл бұрын
Good question! I will try to make a video about it (but much later)
@giovannigiorgio03 жыл бұрын
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?
@aaron92962 жыл бұрын
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!
@yashkhabiya3 жыл бұрын
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!!!!!
@user-sc8sx6pb3i3 жыл бұрын
9:57 Meanwhile in Ace Combat 7 everyone does post-stall manuevers inside tunnels and stadiums!? ('o')
@verticalflyingb7373 жыл бұрын
"trigger's different"
@zyz-pr8bf Жыл бұрын
We have made a propeller and is it possible to determine the lift and drag coefficient through experiments? How can we carry out experiments?
@rushwolf93603 жыл бұрын
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].
@navneetnandakumar89592 жыл бұрын
prisitine!
@modelcraft299 Жыл бұрын
Great 👍
@Ashishkumar-vb7qh3 жыл бұрын
Nice explain 🔥
@samovar93494 жыл бұрын
Hi Aliya!! Will you in the next video mention control systems in Aerospace engineering?
@AliyaBurkit4 жыл бұрын
Hi Almaz, no, not yet. I will make videos on that topic last 😅
@AdilKhan-gc8zu3 жыл бұрын
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
@engineerhubhagwannhi45642 жыл бұрын
Mam your voice is sooo sweet
@sohanroy78333 жыл бұрын
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?
@prajwaldhebe23552 жыл бұрын
PLease if possible also do a video on ejection seats in fighter jet
@joeysipos3 жыл бұрын
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?
@erikjovanovic12765 ай бұрын
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 ?
@shravankhot23563 жыл бұрын
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
@rishabgupta41724 жыл бұрын
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?
@AliyaBurkit4 жыл бұрын
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
@muath14013 жыл бұрын
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?
@posterizedsoul48104 жыл бұрын
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.
@AliyaBurkit4 жыл бұрын
Thanks so much! That's the goal 😊
@posterizedsoul48104 жыл бұрын
@@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.
@AliyaBurkit4 жыл бұрын
Sure
@heshanweerasinghe24472 жыл бұрын
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.
@user-nz3tt1vy6h3 жыл бұрын
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 ?
@zaynbashtash2 жыл бұрын
Is it the flat airfoil (plate)?
@allisongreen35012 жыл бұрын
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?
@abrhamghidey42133 жыл бұрын
May i ask you a question , how do i calculate parasite drag and Oswald effective factor ?
@engineerhubhagwannhi45642 жыл бұрын
Mam can you please make a video on Cp distribution on wing surface
@matt91693 жыл бұрын
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?
@orangetech84193 жыл бұрын
Hey, can Cl for an aircraft wing be less than 0.3 for an Rc aircraft which is capable of lifting 6Kg payload
@emineyldz90933 жыл бұрын
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.
@JosephHarrisArch4 жыл бұрын
Keep it up Aliya!
@AliyaBurkit4 жыл бұрын
Thanks! I will 😊
@DC-fd3vy3 жыл бұрын
You are awesome!
@jovencantada95722 жыл бұрын
a symmetrical one 7:56
@fggfdgdgfdgffdgfrfdg4 жыл бұрын
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
@AliyaBurkit4 жыл бұрын
Good question. I guess I need to make another video about this topic
@Rvk4882 жыл бұрын
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
@thecorbies Жыл бұрын
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.
@shadracknjane26783 жыл бұрын
You remind me of MY A-LEVEL MATHS TEACHER MR. SUNAK; I always think HE IS YOUR GRANDFATHER.
@AliyaBurkit3 жыл бұрын
Haha I taught A-level at some point
@zaynbashtash2 жыл бұрын
But can we write the lifting force as: (cLmax×sin(alpha/2))?
@miguelaphan583 жыл бұрын
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....
@TuongNguyen-ep5eo3 жыл бұрын
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 !
@bencrawshaw12273 жыл бұрын
So how do you work out the coefficient without a wind tunnel.
@AliyaBurkit3 жыл бұрын
Trial and error 😂 in the field
@anbu39643 жыл бұрын
I love you mam for good teaching. Reply me.
@AliyaBurkit3 жыл бұрын
Thank you for watching!
@anbu39643 жыл бұрын
@@AliyaBurkit mm
@anbu39643 жыл бұрын
@@AliyaBurkit I am new subscriber .
@anbu39643 жыл бұрын
@@AliyaBurkit I am studying ame I want clear explanation of co efficient lift.
@AliyaBurkit3 жыл бұрын
Thanks for joining!
@AirlinesDisasterAnalysis4 жыл бұрын
Great !!!
@AliyaBurkit4 жыл бұрын
Thanks!
@brandonparento32093 жыл бұрын
Hi, I have a question. Is drag force usually greater than lift force at a given speed?
@prince_m_h_d25133 жыл бұрын
6:20
@captmulch12 жыл бұрын
The amount of drag (and therefore thrust) force is always smaller than the lift (and therefore weight) force.
@baviquevirechecantepuspace26153 жыл бұрын
You're amazing! :)
@AliyaBurkit3 жыл бұрын
Thanks :)
@felipegangana20253 жыл бұрын
Thanks!! :)
@mohammadal-qudsi44933 жыл бұрын
Maybe sphere would have a lift of 0 at any angle of attack if the sphere is not spinning.
@nritonga38743 жыл бұрын
How to calculate lift for wing plate?
@tzachus2 жыл бұрын
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.....
@hablabuddha4 жыл бұрын
Can you make a video about stall
@AliyaBurkit4 жыл бұрын
Yes I will
@hablabuddha4 жыл бұрын
@@AliyaBurkit Thank You 😋
@iqhwan80062 жыл бұрын
symetrical airfoil?
@emineyldz90933 жыл бұрын
İf we no have lift , we have just angle of attack, how calculate lift coefficient? Can you tell me please?
@AliyaBurkit3 жыл бұрын
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
@emineyldz90933 жыл бұрын
I got it, Thank you.
@daniperson38062 жыл бұрын
i do not have wind tunnel
@itripleo57803 жыл бұрын
Im a 14 yo wanting to make a airplane simulator, thank you!
@AliyaBurkit3 жыл бұрын
Sounds great! You would need to know coding well
@itripleo57803 жыл бұрын
@@AliyaBurkit I can use C# a bit, still learning but now I am using scratch
@itripleo57803 жыл бұрын
@@AliyaBurkit I got it yay
@AkashSingh-es7tp2 жыл бұрын
Symmetric airfoils !!
@vinayreddy62862 жыл бұрын
Symmetrical airfoil
@usamaejaz52644 жыл бұрын
i want to learn aeromatical engineering mam
@AliyaBurkit4 жыл бұрын
Great!
@maheen83172 жыл бұрын
symmetrical airfoil
@tricksbyutkarshjain49792 жыл бұрын
Answer to the question is --" Symmetric Airfoil "
@vlatkopopovski26852 жыл бұрын
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).
@hablabuddha4 жыл бұрын
Symmatrical AirFoil
@AliyaBurkit4 жыл бұрын
True
@jamaicoconcepcion96553 жыл бұрын
I AM HERE TO LEARN. BUT WHY AM I SIMPING ALL OF A SUDDEN
@stereoscienceandtechnology44064 жыл бұрын
What is wind tunnel?
@AliyaBurkit4 жыл бұрын
good question)) I guess I need to explain it in a separate video
@daniperson38062 жыл бұрын
??
@ashrafulalam84024 жыл бұрын
I think a flat airfoil would have a zero angle of attack
@AliyaBurkit4 жыл бұрын
You mean zero lift?
@AliyaBurkit4 жыл бұрын
A flat airfoil could still have an angle of attack
@ashrafulalam84024 жыл бұрын
@@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 ?
@AliyaBurkit4 жыл бұрын
zero angle of attack is just parallel to the ground
@ericschmitt53903 жыл бұрын
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.