Reading about the crash of American Airlines Flight 191, the proximate cause of the final loss of control was the pilots' reduction of the aircraft's airspeed to V2, in compliance with the published procedures for a single engine failure after V1 during takeoff in a DC-10-10; unbeknownst to the pilots, the damage caused when the #1 engine separated from the aircraft had caused the left wing's outboard slats to retract, decreasing the left wing's stall angle, with the result that decelerating to V2 required the aircraft to fly at an angle of attack at which the left wing stalled.

But why would one even want to slow to V2 in the first place? Even if we, like McDonnell Douglas, ignore the possibility of an engine separating from the airplane and damaging it to the process, there are still good reasons to go faster, not slower:1

  • If an engine has failed, there's no way to immediately know whether it's a contained or an uncontained failure; if it's an uncontained failure (which is, unfortunately, a common enough occurrence to demand consideration when designing an aircraft), there's a very good (or bad) chance that the exploding engine (especially if it's a wing-mounted engine, like the DC-10's #1 engine) has damaged the aircraft's flight control systems, in which case you'll want to be flying as fast as possible in order to maximise the control authority of the surviving controls.
  • If there's a chance that whatever caused the first engine to fail could also take out the remaining engines (for instance, contaminated fuel or a flock of birds), you'll want to get as much speed reserve as possible, so that, if the remaining engines do fail, you'll be able to zoom-climb and reach your best-glide speed at the highest possible altitude, thus giving you the most time and space to do something.

What good reason could there possibly be for eroding your already-degraded safety margins yet further by slowing to V2 following an engine failure?

1Not that doing so was justifiable of their part (it wasn't, as the NTSB accident report makes clear).

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    $\begingroup$ I never flew the DC-10, but my first reaction to your question was that if I have airspeed in excess of V2, I'm not climbing as fast as I could. Looking at it from the standpoint of energy management and considering whether to have more speed or more altitude, my gut reaction is that I want the altitude. I can always convert altitude to speed (and altitude is good from the standpoint of obstacle clearance). As you note the extra speed would enable a zoom-climb, but the time spent at the extra speed would have meant more drag than at V2 and that difference would not be recoverable. $\endgroup$
    – Terry
    Feb 17, 2019 at 0:28

2 Answers 2


Simply put, V2 is the speed that guarantees the best angle of climb on one engine. Any slower or faster increases the risk of hitting an obstacle.


There are 2 main categories of drag - induced drag, and parasite drag. Induced drag is an unavoidable consequence from lift and largely shows itself in the form of wake vorticies. Induced drag is largest at high angles of attack - i.e low speed.

Parasite drag includes drag from things like skin friction, rough surfaces, wires, and so on. Parasite drag is largest at high speed.

If you plot both categories of drag together, you end up with a chart like this:

Drag curves - wikipedia

The aircraft must provide enough thrust to overcome the total drag, so this can be renamed the thrust required curve. If you picture a horizontal line across the top of the graph, that would represent the thrust available for a jet engine. The speed which provides the biggest gap between thrust required and thrust available, or excess thrust, is the speed at which the aircraft climbs at the steepest angle.

But if you lose 50% of the thrust available, then that horizontal line moves down a lot. If you are going too fast, the total drag might be more than the available thrust, forcing the aircraft to descend.

That's why V2 exists, to give the pilots a guarantee that at that speed, there will still be enough excess thrust to climb at the steepest possible angle.

It's true, slowing to V2 doomed this flight. But uncontained engine failures, especially ones that damage the wing, are extremely rare, and more rare than that is a dual engine failure for whatever reason. The powers that be decided it is safer to give pilots the V2 target so they don't mess up in an already high-workload scenario and hit a tree.

  • $\begingroup$ So V2 is just another name for Vxse (or whatever the equivalent to that is for aircraft with more than two engines - Vx[n-1]e?). $\endgroup$
    – Vikki
    Aug 26, 2021 at 1:21

V2 by definition is the speed an aircraft will climb with an engine failure. Notice this does not mean further reducing power. The aircraft will pitch to maintain V2 as per procedure with whatever thrust it has.

The crux of the question is how close V2 is to stalling speed in the event of a multiple malfunction. In this case the slats retracted when the engine separated. This was probably an unforeseen scenario. Procedures and design certainly warrant review.

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    $\begingroup$ I wouldn't that much worry about the stall speed, rather the Vmca speed. $\endgroup$ Feb 17, 2019 at 9:18
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    $\begingroup$ The modified engine change procedures devised by the airline to reduce maintenance man-hours (with increased risk of damaging the pylon-to-wing attachment points) certainly needed review, since they were the root cause of the accident! $\endgroup$
    – alephzero
    Feb 17, 2019 at 12:18
  • $\begingroup$ @VladimirF: You should, given that the stall speed is ~30kts above the (purely theoretical) V-MCA. $\endgroup$
    – Vikki
    Feb 18, 2019 at 3:56

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