ATPL POF Theory: Why are wings swept back ✈ Please like, share and subscribe if you found this video useful and would like to see more :) Comment with future video suggestions bellow!
I don’t understand why the air would just take a turn once it reaches the wing. Why would it just turn to the left or right once it reaches the swept back wing?
You’re amazing Ed. Just a quick question, if the air particles accelerate to supersonic speed over the top part of the wing at the thickest point, as you said, than why doesn’t it affect the fuselage of the aircraft which is much thicker than the wing and it’s traveling through the air at the same speed as the wing? Would love to hear back form you Many thanks
Hi Pual, fusolage doesn't have the same wing profile, and for this reason it doesn't act like a wing. So, the flow up the fusolage doesn't take the accelleration as on the upper wing, Then, no problem of sonic speed there. Hope it help.
@Sussy ass motherfucka it would decrease lift. The aircraft would have to travel faster in order to generate the same amount of lift. But making the aircraft go faster is the whole point.
Prepping for an interview and was confused about how to explain this, but helped massively, thanks dude! Haven't studied much POF since ATPL's few years ago LOL
I have completed my ATPLs already, however I have an airline assessment coming up so I am re-visiting some tricky areas. The hardest subject in the ATPLs for me was POF, I found it so confusing, every RU-vid video was just someone reading from a book. Now if there were more videos like this, I would have passed with a better mark! Thank you for this video, you made a tricky topic into something very understandable! We need more instructors like you
Great job PilotEd! Your videos are really amazing! Nice and short and straight to the point. Would you be able to make one of your videos with a stalled swept wing? Describing the wing tip stall in high altitude flying. Best regards, Anders
good question: my explanation may be wrong and actually i asked similar question i think for the spanwise flow: the aerodynamics loads will increase over the wing and this will lead to increase the angle of attack which leads to generate more lift. however i think the spanwise leads to stall and it is underisrable in flight.
@@ammarabdulkadhim8596 i dont think spanwise generates lift thus planes would reduce their spanwose flow and increase chordwise flow to increase the lift. ( f14 , su 17 ) by straightening their wing if they found themselves in a variable sweep wing aircraft
@@moizabdul5384 thats the reason "Wash Out" has been given to wings where the root chord stalls first and outboard of wings will still have enough lift for controllability
Mac Tuck was explained wrong. Its created due to lose of lift on the wing due to Shock Drag ( basically all lift has been washed away back from the wing surface by the fluid shockwaves ) and existing lift on the tail which holds the tail up therefore nose down attitude. 👍🏼
This is the best and the most simple video ever, thank u, but i have problem of fully understanding of what is called center of lift and gravity. Like distance between these 2 points, also how do i find center of lift and gravity??
I’m currently 15 and I would like to be a pilot. As a head start I watch your videos. My question is do you recommend any books or websites for Atpl theory. Also I’m in the uk
why span wise flow cannot accelerate ? 3:17 How we can push the aircraft speed faster since span wise flow doesnot accelerate and we have half of the air only hitting the flowwise?
Great video - subscribed. I have one question though, and it's regarding the Mach Tuck phenomemnon. I am no physicist or mathematician, so forgive me for my slowness. From what I have understood, as the air passes over the trailing edge, it accelerates, leading to an area of low pressure, right? So when the shockwave starts to form, the air behind it decelerates, increases in pressure and density. Shouldn't that lead to an area of high pressure behind the shockwave, leading to it pushing down on the back end of the foil, causing the plane to pitch up? Why does the plane's nose tuck down instead? Thanks for the content.
Actually when mach tuck fist came about it was something completely different, was due to the control getting inverted because of the air pressure on the tail-section! thats for another video :) hard for me to describe via text, ill add it to my list. thanks so much for watching
Because it takes much more power and fuel to go even faster when you’re already going 500+ mph. The extra fuel it would take to go from like 500+ to 600+ is a lot. It saves on fuel and money and the engines will last longer. Imagine everywhere you drove, if you floored it as hard as possible. Even if you get there faster, you’re using exponentially more fuel at higher speeds and wearing your engine out
You explained on your video "how lift is created" that the real reason of lift was the opposite reaction to a force at the trailing edge to the downwash (center of pressure at the trailing edge), however, you are saying on this one that the center of pressure is 25% towards the leading edge (accepting Bernoulli's), and as the center of pressure moves aft, there is a tendency of a nose down attitude. I am a bit confused, may you please develop on that? Thanks!
Really useful and clear explanation Ed, thank you for taking the time to explain and put this up, as well as the others too, many will clearly benefit from these. Just a friendly observation, sometimes the use of a pointer (pen or something similar) is nice when highlighting something on a board. :-)
Thank you very much Sir but I have one slight question which is what is the effect of the spanwise and chordwise flow on the abgle of attack and the stall phenomenon?
@@PilotEd i think there is effect. for example, for the spanwise effect: on angle of attack when the aerodynamics loads increases on the wing, this will lead to stall conditions and all of us know increasing the angle of attack after 16 in some airfoil design will lead to stall phenomenon. what do you think sir, if my explanation is right? however, the other aerodynamics types is still unobvious for me and for that i asked you
