Cyrus Hung

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@Snehorita Ай бұрын

Thank you very much.I was looking for these sort of videos to understand my civil aviation course but couldn't find.

@musicmack Ай бұрын

Nobody knows I'm using this to write a over 1k word essay on the basic shape of a aircraft Hehe

@varshneydevansh Ай бұрын

thansk

@sheezafarooq1007 3 ай бұрын

Good work

@steve_lehr 3 ай бұрын

The tendency of the aircraft to pivot into the relative wind is the result of the airflow on the vertical stabilizer not the rudder.

@rico_cavalierie 5 ай 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.

@b.abdelmoumen4905 6 ай бұрын

Thank u for the video keep up man

@kdr955 6 ай 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.

@VoluntaryPlanet 7 ай бұрын

Aircrafts is not a word

@christopherwilson6527 9 ай бұрын

Aircrafts? Aircraft is singular and plural.

@alphahaze4506 10 ай бұрын

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

@christopherknee5756 10 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.

@commonwombat-h6r 10 ай бұрын

thank you for this informative and helpful video!

@withgrowinginsanity198 11 ай бұрын

Its such a pity you stopped making new videos 😢

@gerrycollins2335 Жыл бұрын

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

@qwerty-yv8wm Жыл 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.

@emilianoramirez5398 Жыл бұрын

What a great video, thank you

@Brandon_Tyr Жыл 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.

@JohnJCB Жыл бұрын

You sound a lot like mini air crash investigation

@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?

@tqaquotes9379 Жыл бұрын

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

@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 ?

@steffenleo5997 Жыл бұрын

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

@ChrisZoomER Жыл бұрын

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

@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.

@Monsoozi Жыл бұрын

Studying for a minor detail in a daydream

@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?

@Brandon_Tyr Жыл 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.

@bernardoloures9848 Жыл бұрын

This was quite helpful. Thanks!

@cristinabadea6201 Жыл бұрын

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

@SoloRenegade Жыл бұрын

3:44 "lowest possible induced drag" false

@Brandon_Tyr Жыл бұрын

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

@SoloRenegade Жыл бұрын

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

@Brandon_Tyr Жыл 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.

@SoloRenegade Жыл 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.

@Brandon_Tyr Жыл бұрын

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

@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.

@david_porthouse 2 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.

@leblblb 2 жыл бұрын

Great content, took lot of notes. Thank you.

@Drunken_Hamster 2 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?

@Maxtherocketguy Жыл бұрын

Swept wings

@anastasiaejike6020 2 жыл бұрын

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

@leoe-smooth3073 Жыл бұрын

Thank you 'at all'

@startupusingthelens 2 жыл бұрын

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

@simpilot001 2 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

@myusername3689 2 жыл бұрын

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

@dylanklein3872 2 жыл бұрын

BEAUTIFUL VIDEO

@kirisaki_chan 2 жыл бұрын

This is very helpful and informative, thank you!

@tk754 2 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.

@sailingjabulani Жыл бұрын

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