Пікірлер

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  @richard_the_lion_farted12 күн бұрын

  Right from the rectangular planform I had a nagging question. Does a straight wing start to stall at the root and then have the area of the stall radiate out due to the planform? I thought it was due to the typical built-in angle of incidence that is greater at the root and is reduced as it moves out to the tip by means of a long twist.

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  @b.abdelmoumen4905Ай бұрын

  Thank u for the video keep up man

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  @kdr955Ай бұрын

  At 4:30 you show Centripetal force as equal and opposite to a “Reaction” force. If this were true, then these forces would cancel each other out and the aircraft would fly straight ahead, i.e. no turn.

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  @VoluntaryPlanet2 ай бұрын

  Aircrafts is not a word

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  @christopherwilson65274 ай бұрын

  Aircrafts? Aircraft is singular and plural.

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  @alphahaze45064 ай бұрын

  People like you, is what the world deserves. thank you

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  @christopherknee57565 ай бұрын

  The plural of aircraft is NOT aircrafts. It is aircraft. Example: There were 2 aircraft on the runway in Japan, one more than is safe.

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  @user-qp2ps1bk3b5 ай бұрын

  thank you for this informative and helpful video!

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  @withgrowinginsanity1986 ай бұрын

  Its such a pity you stopped making new videos 😢

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  @gerrycollins23357 ай бұрын

  I was surprised to see that delta wings weren't included in the discussion.

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  @qwerty-yv8wm8 ай бұрын

  I think the formula for lift that you've showed is wrong, because Lift=1/2*density*area*velocity^2*Cl You used pressure instead of density.

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  @emilianoramirez53988 ай бұрын

  What a great video, thank you

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  @Brandon_Tyr9 ай бұрын

  I know this is 3 years old now but @4:38 I think your graph is backwards? The blue would be the elliptical planform and lift profile. The yellow does not look ellipitical, instead it looks like a smoothed corner rectangle, which is the lift profile of a rectangular wing. Oh just continued watching, it's worse than I thought, you continue on saying the elliptical plan form provides a uniform lift profile... You should make a correction announcement in a pinned comment at the least. It's very misinformative. You also say swept wings only advantage is lower transonic drag, but they have other advantages as well. They provide roll stability, the same way positive dihedral would. Swept wings then require no or less dihedral angle.

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  @JohnJCB10 ай бұрын

  You sound a lot like mini air crash investigation

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  @CultureTripGuide-HilmarHWerner Жыл бұрын

  I miss an assessment of tapered wings with leading edges rectangular to the fuselage and with only the trailing edges being tapered. what's the effect on drag? and a description of the effects of foreward swept wings on drag?

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  @tqaquotes9379 Жыл бұрын

  Types of Stabilities (and Instabilities) in Aircraft Dynamics usman032.blogspot.com/2023/05/types-of-stabilities-and-instabilities.html

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  @steffenleo5997 Жыл бұрын

  Good Day, in normal flight condition i think using an elevator for a turn is almost impossible or i missunderstand something on your video 7:20 ?

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  @steffenleo5997 Жыл бұрын

  Great videos... 👍👍...thank you so much

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  @ChrisZoomER Жыл бұрын

  There’s also wave drag which arises from shockwaves at transonic and supersonic speeds.

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  @ChrisZoomER Жыл бұрын

  Swept wings actually reduce drag at all speeds because some of the air flows along side the wing because they angle backwards much like sliding down a ramp instead of running into a wall. This also reduces lift because air flowing along side the wing doesn’t produce lift like the air flowing directly over the wing does, so swept wings are only fit for high speed flight.

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  @Monsoozi Жыл бұрын

  Studying for a minor detail in a daydream

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  @tomwaltermayer2702 Жыл бұрын

  Wish you'd explained how it might be possible to make an elliptical with benign stall characteristics and great strength. Or did R. J. Mitchell have a secret sauce unknown others before or since?

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  @Brandon_Tyr9 ай бұрын

  A cleverly chosen combo of camber and twist and thickness can make even a rectangular plan form give an elliptical lift profile. So it is likely camber and twist and thickness have been chosen to have better stall characteristics.

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  @bernardoloures9848 Жыл бұрын

  This was quite helpful. Thanks!

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  @synergy6294 Жыл бұрын

  Recently the Mystery of Airfoil 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.

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  @cristinabadea6201 Жыл бұрын

  super good and useful material. thank you for your patience, help & time!

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  @SoloRenegade Жыл бұрын

  3:44 "lowest possible induced drag" false

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  @Brandon_Tyr9 ай бұрын

  Its true in 2D flat land! Too bad no planes are 2D >.>

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  @SoloRenegade9 ай бұрын

  @@Brandon_Tyr nope, there are still other ways to reduce induced drag in 3D as well.

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  @Brandon_Tyr9 ай бұрын

  @@SoloRenegade Yup, definitely. Camber, thickness, and twist can all effect Di and the lift profile. My response earlier was just to bring up WHY people say elliptical planforms give the lowest Di. 2D aero analysis gives that result.

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  @SoloRenegade9 ай бұрын

  @@Brandon_Tyr but you still haven't listed the Best way to reduce induced drag (well, you did indirectly I suppose). but I'm not surprised, next to no one knows about it still.

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  @Brandon_Tyr9 ай бұрын

  @@SoloRenegade TBH I'm not sure what the "best" way is, or even if there is a best way.

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  @marcot1683 Жыл бұрын

  Thanks so much for such a decent video. This is even better than what we get at the aviation academy in England.

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  @david_porthouse Жыл бұрын

  The immediate effect of increasing the angle of attack is that air has to double back round the trailing edge to join the rear stagnation point. This is possible for a superfluid such as liquid helium, but not for a viscous fluid like air. Instead there is a flow separation at the trailing edge and vorticity is dumped in the flow. By the topological principle of conservation of vorticity there must be extra bound vorticity of opposite rotation associated with the aerofoil, and this generates extra lift. This extra lift can be explained formally in terms of the Kutta-Joukowski circulation theorem, or informally as the Magnus effect. Note that equal transit time theory is true for liquid helium, but false for liquid sodium. No lift is generated in liquid helium.

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  @leblblb Жыл бұрын

  Great content, took lot of notes. Thank you.

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  @Drunken_Hamster Жыл бұрын

  What about tapered wings that are swept, but only enough to make either the leading or trailing edges straight/perpendicular to the direction of flight?

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  @Maxtherocketguy Жыл бұрын

  Swept wings

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  @anastasiaejike6020 Жыл бұрын

  You didn’t do a bad job at all. Thank you for putting this information out and not rushed at all.

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  @leoe-smooth3073 Жыл бұрын

  Thank you 'at all'

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  @ThinkAi123 Жыл бұрын

  Thank You very much, for uploading such good quality videos.

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  @simpilot0012 жыл бұрын

  So not only does this person do aviation, they do game dev as well. It is so interesting how if you have one thing in common you are fairly likely to have another

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  @myusername36892 жыл бұрын

  The tapered wing is typically used with a washout airfoil design to reduce the stall and spin problems.

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  @dylanklein38722 жыл бұрын

  BEAUTIFUL VIDEO

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  @kirisaki_chan2 жыл бұрын

  This is very helpful and informative, thank you!

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  @tk7542 жыл бұрын

  Minumum sink speed wont give the longest distance on horizontal path with given altitude or time. I think there is a mistake at that point of explanation. You should check it from different sources. But anyway. Your videos are greatly appreciated. Keep doing friend.

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  @sailingjabulani Жыл бұрын

  correct, min sink gives longest time before reaching the ground, while best L/D gives furthest distance before reaching the ground.

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  @mohammedpilot23352 жыл бұрын

  Thanks

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  @jekekefe59232 жыл бұрын

  Thank you for posting this I just subscribed

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  @21trips2 жыл бұрын

  Which wing planforms have the best glide ratio?

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  @myotherusername92242 жыл бұрын

  Higher aspect ratio, better glide. Look at sail planes

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  @technicalyoutube59982 жыл бұрын

  Sir can you reply me

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  @technicalyoutube59982 жыл бұрын

  Sir how to calculate CG of swept wing please please please reply

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  @Fuck_You_Youtube_ Жыл бұрын

  Never.

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  @letholeproductions78742 жыл бұрын

  highly underrated narrator on KZread for aeronautics and aerodynamics.

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  @stevefernando22863 жыл бұрын

  Nice video. And good explanation.

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  @saptarshibhowmik28343 жыл бұрын

  Very easily explained with lots of information which are actually needed. Please keep on publishing new videos on new topics. Thanks

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  @dannymomo60043 жыл бұрын

  This is rather pogchamp

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  @jaygongetemwdym37303 жыл бұрын

  You may not have thousands of views, but I can guarantee you this is Quality Content,

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  @cyrushung69463 жыл бұрын

  Thanks so much!

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  @suilujraupe6504 Жыл бұрын

  Didnt age well

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  @Maxtherocketguy Жыл бұрын

  @@suilujraupe6504 15,371 views

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  @guillermobarrios8605 Жыл бұрын

  😂😂 15k but not enough to match the quality of this content. Only explanation that made it easy to visualize and understand.

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  @Maxtherocketguy Жыл бұрын

  @@guillermobarrios8605 yep

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  @arrogant2193 жыл бұрын

  I love you ❤️❤️

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  @thesparkians48594 жыл бұрын

  It was a good info about wing plan forms. thanks!

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  @gazitaspnar92964 жыл бұрын

  thank you for the video but why did not we take into account the wave drag (results from shock waves)?

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  @cyrushung69464 жыл бұрын

  Hi Gazi! I did explain wave drag in one of the later videos (planforms) but neglected to talk about it for this video. I'll probably re-upload this video in the future with wave drag added in. Thanks for pointing that out!