From other answers I've gathered that stall occurs when the air flow separates from the wing surface. And also that this starts at the back of the wing and progresses forward as AOA increases.

Is this process not uniform? What causes the buffeting just under the stall AOA? Is it simply the turbulence behind the point of separation?

Also, what factors, such as speed, altitude or air density affect the amount of buffeting?

  • 1
    $\begingroup$ This may also have to do with the "twist" in the wing, the chord angle (AoA) closer to the root of the wing is different than the chord angle near the tips on some aircraft (like a Cessna 172). This means as the stall progresses, the root of the wing stalls first, and the tips last, I was told this is for aileron effectiveness during a stall. This could contribute to the buffet as basically the points of lift move further out as the stall progresses. $\endgroup$
    – Ron Beyer
    Commented Jan 8, 2016 at 19:19

2 Answers 2


This article states it pretty well (better than I can word it).

When the angle of attack (AOA) of the wing increases, the point where the airflow separates will move forward and the streamlined airflow will become turbulent and separate from the wing. This turbulent wake then meets the aft fuselage and tail section of the aircraft. This will be felt by the occupants of the aircraft as a rumble or buffet. Not all aircraft have a pronounced buffet, this depends on the size and location of elevator.

Interestingly enough you can also induce a stall (and first high speed buffeting) by gong too high and too fast while trying to maintain level flight which will cause the center of lift to move aft along the wing. Basically your stall speed and your critical mach number eventually converge this is known as the coffin corner. There is a nice discussion on it here.


Not all stalls start from the trailing edge and progresses forward. In general, three types of stall are described:

  • Trailing edge stall- This is the preferred stall characteristic; The turbulent separation point moves forward from the trailing edge with increasing angle of attack. usually found in airfoil sections with thickness ratios 0.15 and greater.

  • Leading edge stall- The flow separates abruptly from the leading edge without subsequent reattachment; usually found in airfoils with thickness ratios between 0.09 and 0.15.

  • Thin airfoil stall- Found in airfoils with small thickness (< 0.09), the separation occurs at the leading edge and the flow reattaches at a point which then moves progressively rearward with increase in angle of attack.

Buffet is a kind of vibration caused by aerodynamic excitation, usually associated with separated (or turbulent) airflow. As the aircraft approaches stall, the airflow over the wing becomes turbulent and if it flows across the horizontal stabilizer, buffeting may occur.

Whether low speed (stall) buffet happens or not depends on the aircraft characteristics; for example, the stall starts from the root in case of straight wings and the stabilizer is affected by the turbulent airflow before the outer wing stalls- this can be used by the pilot to take corrective action (as @Ron Beyer points out in his comments). In case of swept wing aircraft, the stall progresses the other way around- from tips to rot and it will be difficult for the pilot to use buffet in any real sense.

This buffeting can act as a warning for the pilot that the aircraft is approaching stall and he/she has to take corrective action. In aircraft that do not show this behavior, some warning cues, like stick shaker are sometimes incorporated in order to warn the pilot.

As density altitude increases, the angle of attack required to produce turbulence at the top of the wing (stall angle) decreases till a point is reached that the high speed buffet (Mach buffet, due to supersonic airflow) and the stall buffet (as already explained) converge. This point is called the coffin corner.

Coffin Corner

"CoffinCornerU2" by Department of Defense - AF (C)-1-1, Flight Manual, Models U-2C and U-2F aircraft. Page 6-11. Licensed under Public Domain via Wikipedia.

From FAA Handbook FAA-H-8083-3A:

An airplane’s indicated airspeed decreases in relation to true airspeed as altitude increases. As the indicated airspeed decreases with altitude, it progressively merges with the low speed buffet boundary where prestall buffet occurs for the airplane at a load factor of 1.0 G. The point where the high speed Mach indicated airspeed and low speed buffet boundary indicated airspeed merge is the airplane’s absolute or aerodynamic ceiling. ... the airplane can neither be made to go faster without activating the design stick puller at Mach limit nor can it be made to go slower without activating the stick shaker or stick pusher. This critical area of the airplane’s flight envelope is known as “coffin corner.

  • $\begingroup$ Wow, that leading edge stall sounds kind of nasty. Can you give an example of an aircraft that exhibits that type of stall behavior? And on the thin airfoil stall, when the flow reattaches does that shift center of pressure backward causing a nose down? $\endgroup$
    – TomMcW
    Commented Jan 9, 2016 at 2:12
  • $\begingroup$ @TomMcW You're correct that in case of thin airfoil stall, there is an increase in the nose down pitching moment as the separation bubble envelopes more of the the airfoil upper surface. For Reynolds number range of normal operating conditions, leading edge stall is found in some helicopter rotors. $\endgroup$
    – aeroalias
    Commented Jan 9, 2016 at 16:57
  • $\begingroup$ @aeroalias I liked the ref. from the FAA handbook but you seem to have confused turbulence and turbulent flow with stall [...the angle of attack required to produce turbulence at the top of the wing (stall angle)...]. The flow before detaching can be either laminar or turbulent, this is a state of the flow. I mean that in cruise attitude, you have a small laminar part near leading edge and then the flow transitions to turbulent being fully attached to the wing. $\endgroup$
    – ares
    Commented Oct 14, 2017 at 1:37

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