Don’t be concerned with that poster’s statement.
I’m sure he was trying to point out what he thought the rules were, probably for your benefit, as there are sections of the forum (Bugs & Issues) where the moderators do not want you to post without doing a search for your question in the rest of the forum sections first.
Did all this info answer your question?
Lift depends on AOA, speed (squared), air density and the shape of the wing. Not only AOA. That’s why the slower you fly the higher you need to keep the nose to maintain altitude.
I don’t think anyone meant to offend you.
It was your statement “Sorry, but questions like this should go through google first”
This implies that the poster should not have posted here until he did a google search first.
That is incorrect.
Your idea was good, had you “suggested” the user to google it, not “told” the user he was wrong to post here first.
And you were correct, a google search did answer his question.
Don’t get discouraged from helping here, or thinking people are dumping on you.
All advice here is welcomed, you probably should be just a bit more tactful with your post’s wording.
Many things can be googled and many things can be googled wrong. Google just presents us things that other people have written and with regards to aviation theory, aerodynamics, air law(s) etc there are maaaany opinions out there and many many are simply wrong.
I’ve seen a statement of a “youtube pilot” that the flaps positions written on the flaps lever of the aircraft he flies are actual flap angles which is totally wrong but a LOT of people believe it now, after all he has the stripes in his videos.
So asking a question lke this in a corresponding forum is totally fine, the best he will get is a good explanation, the worst is a dozen wrong answers that disagree with each other. But here he can ask back and it can be discussed, other than “out there”.
No need to be pouty now. Take it as a disagree with you, nothing bad has happend. =)
There is a term often used on the net, RTFM.
Many times the answer is there but not necessarily in a format that a mere mortal could understand.
Hence a flippant, Google it, rightly causes concern but does not help the Op.
I was brought up to listen and to help others but today it seems more and more people are becoming far less tolerant to others.
If you can offer constructive comment that will not cause offence, post it, if not, move on without comment.
There is a quote … better to remain silent and be thought a fool than to speak out and remove all doubt.
Hi there, Yes it did. Thank you.
I responded to the disingenuous ‘sorry’ as in ‘sorry - not sorry’ that was used to discourage the asking of a valid question in a public flight sim forum.
No one ‘demonized’ you. From what I see the people that responded to your reply seem to be pointing to the lack of patience / tolerance of it - and not to your personal character.
…this especially after the OP felt obliged to apologize for asking it.
nothing personal
“I have a question ,what is AOA?”
29 replies and not a single one answered the question?
AoA is simply the angle of the relative wind over the wing. Once you hit the ‘critical’ AoA your wing will stall and things on the ground get bigger…not a good thing if you are too close to it ! 
Keep asking questions!
Did you see the 1st post after the OP? Or the 4th one? 
Did you see the 1st post after the OP? Or the 4th one?
Yup, but they took him ‘off site’, I tried to answer here for him.
Its very simple, dont need a video or a long essay on the subject of AOA.
High AOA, bad, will stall once you go over. Low AOA good. Its a measure of the angle of the wind hitting the leading edge.
I remember the movie TOP GUN, Where they had a jet loss, Is that the same thing as AOA?
This is a forum. To ask questions. Let them ask.
oh oh - a TOP GUN reference…If I recall the ‘incident’ you’re asking about - that was a right engine compressor stall while at high speed, induced by the jet exhaust or ‘jet wash’ of the F-14 flown by Ice Man lol - the loss of power to the right engine caused a flat spin (plane rotates at high speed around the vertical axis - like a disc) which was unrecoverable.
Compressor stall is when the blades of a jet turbine lose their ‘lift’ either by angle of attack or the absence of airflow
The angle between the relative wind, and the chordline of the wing. Good question. Cfi
Good answer to a good question! The thing to understand is what AOA (or alpha, as it is often referred to) is appropriate for your condition. Climbing out or leveled off, your AOA should be very low (the plane is going where it is pointed). On approach, you may have a positive pitch angle (above the horizon), but still be descending. That would be an (appropriate) high AOA. Looking at lift curve can help you visualize it. The other poster was correct, by the way - high AOA requires more caution, as you are approaching your stall speed.
As others stated above, AOA means “angle of attack” and is the angle between the wing chord line and the relative airflow (i.e. the air flowing over the wing).
As you know, lift is - simplified - created by air flowing above and below the wing creating a relative low pressure on the top of the wing and a relative high pressure under the wing. The faster the wing moves through the air (represented as IAS/TAS), the greater is the difference between the pressures above and below the wing, and the higher is lift at a given angle of attack.
You can try this out very easily: Take any aircraft (e.g. a C172), take off and try to maintain a level flight (maintain altitude) while changing speed. The faster the aircraft is, the more you will have to lower the nose in order to prevent the aircraft from climbing - you are reducing the angle of attack (and thus reduce the lift caused by the AOA). Vice versa, the slower the aircraft flies, the more you will have to pitch up in order to prevent the aircraft from losing altitude - you are increasing the AOA (and therefore increase the lift).
At one point, the AOA will be too high: the air flowing above the wing will separate from the wing’s surface too early and the wing can no longer create any lift - the wing stalls. AFAIK, a wing of a commercial aircraft typically creates lift at an AOAs of between ~-4° and +11° (depending on the actual aerodynamic form of a wing, there are
For the sake of completeness, please note that stall rather is a matter of AOA and not so much of speed - you can stall your aircraft at high speeds, too. If you change the aircraft’s pitch too quickly at high speeds, this can also result in a too high AOA, and thus a stall (for example, it may be caused by a too harsh recovery after a spin - sometimes referred to as “secondary stall”).
In order to clearly identify a flight condition where a stall may occur, the most reliable indication is AOA - not speed. This is one of the reasons why, for example, Boeing’s infamous MCAS relied on the data provided by AOA-sensors (unfortunately: only one sensor without backup) instead of speed.
If you are interested on this topic, I also recommend reading on the crash of Air France flight 447 (AF447). Confusion about the aircraft’s speed and angle of attack (and the lack of an AOA indicator in the cockpit) played a significant role in this tragedy.
It’s really the vacuum or the lack of pressure on the top of the wing that provides lift. A flat bottom wing doesn’t produce more pressure on the bottom of the wing unless it is at an angle. Air has more distance to travel on top of the wing due to the airfoil causing less pressure. You are correct that relative pressure is lower on top than bottom.
it might help matters to just post this link for ALL
it was written for FS2002 but it still fully applies here
MS FLIGHT SIMULATOR 2002 GROUND SCHOOL : Free Download, Borrow, and Streaming : Internet Archive
It’s not a theory or a myth, it’s fact. Ultimately, the lift is caused by the difference in pressure on the bottom and top of the wing. In a asymetric wing with airfoil on top and flat bottom, there is no addiitonal pressure on the bottom of the wing compared to it’s environment when it is traveling in exact horizontal plane. In this case, the lift is caused by the “vacuum” on the top of the wing caused by shape of the airfoil. If you have a symetric wing, then you need angle the wing (leading edge higher) for lift …which also causes less pressure on the top of the wing than the bottom. At any rate, you’re not way off.