Відео

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.

Thank u for the video keep up man

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.

Aircrafts is not a word

Aircrafts? Aircraft is singular and plural.

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

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.

thank you for this informative and helpful video!

Its such a pity you stopped making new videos 😢

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

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.

What a great video, thank you

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.

You sound a lot like mini air crash investigation

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?

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

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 ?

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

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

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.

Studying for a minor detail in a daydream

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?

This was quite helpful. Thanks!

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

3:44 "lowest possible induced drag" false

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

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.

Great content, took lot of notes. Thank you.

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?

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

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

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

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

BEAUTIFUL VIDEO

This is very helpful and informative, thank you!

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.

Thanks

Thank you for posting this I just subscribed

Sir can you reply me

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

highly underrated narrator on UA-cam for aeronautics and aerodynamics.

Nice video. And good explanation.

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

This is rather pogchamp

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

I love you ❤️❤️

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

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

Love your content