Design maneuvering speed, VA, is a valuable tool in any fighter pilot's arsenal. Knowing how to extract the last bit of aerodynamic maneuverability can be a lifesaver in air-to-air combat. It is, however, a subject best left in the classroom for most transport category pilots. It is defined in 14 CFR 25.335 as simply the clean stall speed of an aircraft times the square root of its positive maneuvering load factor limit. Aircraft designers must consider it, but manufacturers are not constrained on how they present it. While the layman's translation of VA is the speed at which you cannot stall or over-stress an aircraft, manufacturers do not have to specify an altitude or weight at which they figured VA. Pilots are either left with a single number without the weight and altitude specified, or a chart that is hardly usable when the pilot wants to know a speed to fly.
There is limited benefit to a transport category pilot knowing a specific VA, and there is a real danger if pilots don't understand the true meaning of VA. The old maxim that you can "yank and bank to your heart's content at VA" is false. Pilots should understand:
So what does this mean to us transport category pilots? Fly with some finesse, for every action there is a reaction, give the airplane time to talk back to you. (And listen!)
Everything here is from the references shown below, with a few comments in an alternate color.
The published VA in your flight manual is a regulatory requirement from 14 CFR 25. It stipulates that the aircraft flaps are retracted but allows the manufacturer to choose a weight and altitude with no further conditions:
[14 CFR 25.335 Design Airspeeds] The selected design airspeeds are equivalent airspeeds (EAS). Estimated values of VS0 and VS1 must be conservative.
(c) Design maneuvering speed VA. For VA, the following apply:
(1) VA may not be less than VS1 √n where—
(i) n is the limit positive maneuvering load factor at VC ; and
(ii) VS1 is the stalling speed with flaps retracted.
(2) VA and VS must be evaluated at the design weight and altitude under consideration.
(3) VA need not be more than VC or the speed at which the positive CN max curve intersects the positive maneuver load factor line, whichever is less.
Note that 14 CFR 25 does not specify an altitude or weight for Va, but clearly the speed at which the aircraft will stall changes with both of these factors. While the regulation does specify a clean configuration, clearly you will also have different VAs for various gear and flap settings.
Figure: V-G Diagram, from Dole, pg. 193
[Dole, pg. 193-194] An interesting point on the V-G diagram is the intersection of the aerodynamic limit line and the structural limit line. The aircraft's speed at this point is called the maneuver speed, commonly called the corner speed. At any speed below this speed the aircraft cannot be overstressed. It will stall before before the limit load factor is reached. Above this speed, however, the aircraft can exceed the limit load factor before it stalls. At the maneuver airspeed the aircraft's limit load factor will be reached at the lowest possible speed.
From this explanation it becomes clear what matters to a pilot: VA is the speed below which the aircraft cannot be overstressed and above which the aircraft cannot be stalled. But aerodynamic texts that deal with this are usually written with smaller aircraft in mind and the theory breaks down in real life.
Even with smaller jet aircraft we were cautioned to be careful about combining inputs in two or three axis. When I was in the Air Force "yank and bank" community we lost more than a few aircraft to a pilot pulling more rolling G-forces than the aircraft could take. The pilot was within published G-limits, but dead nonetheless.
History has also taught us that the theory breaks down when reversing a control input.
See the case of: American Airlines Flight 587.
If you would like to know more about maneuvering speed and how it is computed, see: Operating Flight Strength.
Figure: Example V-G Diagram, from Eddie's notes.
Gulfstream does not give you anything more than this when it comes to maneuvering speed: VA = 206 knots. But you know that with the flaps up you have a 2.5G limit and your VA will be 1.58 VS and that with the flaps extended you have a 2.0G limit and a VA of 1.41 VS. You also know that you can always see your VREF on the display controller and that your VA will be 15% higher.
How do you know all this? See: G450 Maneuvering Speed.
Figure: Global 6000 VA, from Bombardier Global 6000 Flight Crew Operating Manual, Volume 1, §02-06-3, Figure 02-06-2.
If you don't have a ready display of a comparable speed you should come up with a mental crutch you can use in a pinch. I've never flown a Global 6000 but I would be tempted to say this: Maneuvering speed is equal to twice the grossweight (in thousands) plus the altitude (in thousands) plus 80. At 70,000 pounds and 20,000 feet, for example, VA is about 2(70) + 20 + 80 = 240 knots. Pretty close, eh? It's better than flailing around with no idea at all.
So how would I use this in real life? I think I would add it to my one hour checks, making note of what my VA is each hour.
Hey Eddie! Are you really this paranoid?
A pilot's over-aggressive use of the rudder may have been abetted by the knowledge they were below design maneuvering speed. The case of American Airlines 587 provides a good case study:
More about this: American Airlines 587.
Of course the immediate answer is a question: "Who cares?" So long as you fly your airplane with a degree of finesse you can feel and listen to how the airplane is reacting to your inputs. Being a great pilot you will of course never get close to the stall or G-limits.
I can think of one instance where being nearer to VA can come in handy for us not in the "Get in the bad guy's six" community. If you are in severe turbulence — turbulence so bad you fear structural damage — flying at VA can save your airplane (and hide).
For other aircraft I can't help you other than to say you need to think about it. If you really don't have anything else available to you, it would be good to know a range of speeds.
14 CFR 25, Title 14: Aeronautics and Space, Federal Aviation Administration, Department of Transportation
Dole, Charles E., Flight Theory and Aerodynamics, 1981, John Wiley & Sons, Inc, New York, NY, 1981.
Gulfstream G450 Airplane Flight Manual, Revision 35, April 18, 2013.
Gulfstream G450 Aircraft Operating Manual, Revision 35, April 30, 2013.
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