Operating Flight Strength (Vg / Vn Diagrams)
The operating flight strength of an airplane is presented in the form of Vg or Vn diagrams, where the "V" denotes airspeed and the "g" or the "n" denotes load factor. You might find a Vg diagram in your flight manual if you are flying a high performance fighter. The Vg diagram leads you to cornering speed and that allows you to extract maximum performance from your aircraft without breaking it.
A surprising amount of the science of maneuvering flight still applies to us in corporate and airline aviation. Using a Vg diagram, for example, tells me a most Jets cannot really pull 2 G's at most landing weights on approach, it will stall first. I've never seen a Vg diagram published in any airplane without an ejection seat. Of course if you fly your airplane with a minimum level of finesse you may never need such a chart. But if you would like a chart, you have what you need to build one.
A surprising amount of the science of maneuvering flight still applies to us in corporate and airline aviation. Using a Vg diagram, for example, tells me a most Jets cannot really pull 2 G's at most landing weights on approach, it will stall first. I've never seen a Vg diagram published in any airplane without an ejection seat. Of course if you fly your airplane with a minimum level of finesse you may never need such a chart. But if you would like a chart, you have what you need to build one.
 Vg Diagrams, Theory
 Vg Diagrams and VA (Maneuver Speed)
 Constructing Vg Diagrams, Theory
 Constructing Vg Diagrams, Example
Vg Diagrams, Theory
Load factor in many classic texts is labeled "n" but have become "G" in keeping with pilot phraseology.

Flight strength diagram


Significance of the Vn diagram

VP=VS√n limit
where
VP = maneuver speed
VS = stall speed
n limit = limit load factor
 There are two points of great importance on the Vn diagram of [the figure]. Point B is the intersection of the negative limit load factor and line of maximum negative lift capability. Any airspeed greater than point B provides a negative lift capability sufficient to damage the airplane; any airspeed less than point B does not provide negative lift capability sufficient to damage the airplane from excessive flight loads. Point A is the intersection of the positive limit load factor and the line of maximum positive lift capability. The airspeed at this point is the minimum airspeed at which the limit load factor can be developed aerodynamically. Any airspeed greater than point A provides a positive lift capability sufficient to damage the airplane; any airspeed less than point A does not provide positive lift capability sufficient to cause damage from excessive flight loads. The usual term given to speed at point A is the "maneuver speed," since consideration of subsonic aerodynamics would predict minimum usable turn radius to occur at this condition. The maneuver speed is a valuable reference point since an airplane operating below this point cannot produce a damaging positive flight load. Any combination of maneuver and gust cannot create damage due to excess airload when the airplane is below the maneuver speed.
 When I learned this in 1979 there was a well known caveat that was articulated this way: "Maneuver speed protection is not available for a rolling pull up." In other words, if you combine roll with pull, all bets are off. After the crash of American Airlines 587 it has been articulated in another, more useful way: Maneuvering speed is valid only when considering pitching moments with no aileron or rudder input. The old school house wisdom that "you cannot stall or overstress an airplane at VA is wrong. The formula for VA deals only with pitch and stall speed varies with g (you can stall an airplane above VA if you increase the load factor.
 The maneuver speed can be computed from the following equation:
VP=VS√n limit
where
VP = maneuver speed
VS = stall speed
n limit = limit load factor
 Of course, the stall speed and limit load factor must be appropriate for the airplane gross weight. It is vitally important to realize this number is valid only for the computed gross weight, altitude, and configuration.
Vg Diagrams and VA (Maneuver Speed)
An interesting point on the Vg diagram is the intersection of the aerodynamic limit line and the structural limit line. The aircraft's speed at the 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 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 airspeed. Notice that nothing in the text or the diagram references altitude or weight. The aircraft obviously stalls at a different speed for varying altitudes and weights, and the available G changes as well. The VA published in your flight manual has more to do with the FAA's certification rules than it does about actually maneuvering your aircraft. For now, just realize that the published maneuvering speed in your aircraft flight manual is not what you think it is. 
Maneuver (corner) velocity

Constructing Vg Diagrams, Theory
The Vg Diagram, a plot of the aircraft's available load factor (G) versus velocity (V), is a fundamental tool in determining aircraft performance, most notably its cornering speed.
To an air combat pilot, cornering speed is the point where the pilot can pull in the pitch axis without fear of stalling or overstressing the aircraft, producing the tightest possible turn. (An airplane pulls its way around a turn, the roll only serves to point the pitch vector.) To a corporate or airline pilot, this speed is known as Maneuvering Speed, VA and provides a topic for discussion but little more. To construct a Vg diagram, you must first plot the stalling speed of the aircraft at various load factors. Note that this speed changes with weight an altitude, so you will need a different chart for every combination of weight and altitude that interests you. How do you compute stall speed for other than 1G flight when that is all the aircraft flight manual gives you? With mathematical slight of hand. 
First stage construction of Vg diagram

VS=VS(1G)√G
I took the absolute value of G because we will be dealing with negative G's and you can't very well be dealing with imaginary numbers when talking about maneuvering speed. There is a mathematical justification for this, but for the life of me I can't remember it. But it works.
The second step in constructing a Vg diagram is to plot the positive and negative load factor limits. This tends to be fairly straight forward.
Second stage construction of Vg diagram
The third step in constructing a Vg diagram is to add the limiting speed.
The fourth step is to add maneuvering speed, which occurs at the intersection of the positive load factor limit and the aerodynamic stall line.
The fourth step is to add maneuvering speed, which occurs at the intersection of the positive load factor limit and the aerodynamic stall line.
Third and fourth stage construction of Vg diagram
Constructing Vg Diagrams, Example
The VA maneuvering speed in your flight manual is just a number picked by your manufacturer to satisfy the requirements of 14 CFR 25.335 which only requires the speed cannot be less than the stalling speed of the aircraft with the flaps retracted and does not specify a weight or altitude. If you would like the maneuvering speed for any other configuration, weight, or altitude, you will need to construct a Vg diagram for those conditions.
There is an increased emphasis on maneuvering aircraft in an Unusual Attitude situation and some are advocating that flying at VA gives you a license to maneuver to your heart's content. It does not but studying a Vg diagram helps you understand your aircraft's operating envelope.
I shall construct three Vg diagrams and derive VA for a Gulfstream G450 for these conditions as a demonstration for others wanting to do the same, and to provide the numbers for myself:
I'll go through the steps in detail for the first example and then more quickly for those that follow.
There is an increased emphasis on maneuvering aircraft in an Unusual Attitude situation and some are advocating that flying at VA gives you a license to maneuver to your heart's content. It does not but studying a Vg diagram helps you understand your aircraft's operating envelope.
I shall construct three Vg diagrams and derive VA for a Gulfstream G450 for these conditions as a demonstration for others wanting to do the same, and to provide the numbers for myself:
 Typical Landing at 1,000' Pressure Altitude (Gear Down, Flaps 39°, 50,000 lbs)
 Heavy Weight Takeoff at 1,000' Pressure Altitude (Gear Up, Flaps 20°, 74,600 lbs)
 Heavy Weight Climb at 3,000' Pressure Altitude (Gear Up, Flaps Up, 70,000 lbs)
I'll go through the steps in detail for the first example and then more quickly for those that follow.
Landing  Stall Charts
Using the chart provided by Gulfstream, we see the flaps 39° stall speed at 50,000 lbs and 1,000 feet pressure altitude is 98 KCAS.
Using the chart provided by Gulfstream, we see the flaps 39° stall speed at 50,000 lbs and 1,000 feet pressure altitude is 98 KCAS.
G450 Stall Speed, Idle Power, Speed Brakes Retracted, Flaps 39°
Landing  Derive Range of Stall Speeds for GEnvelope
Recall that
VS=VS(1G)√G We can use that formula to derive a range of stall speeds for varying G loads: G VS 0 0 0.5 69 1.0 98 1.5 120 2.0 139 We plot that on a graph of load factors on the vertical axis and speeds on the horizontal axis. We can fit a curve to replace the dots. Because of the stall chart value was rounded to the nearest 1 knot, errors are magnified on this chart so the curve may not fit exactly. As will be clear a few steps later, the critical bit is the KCAS for the load factor limit. 
Landing  Add GLimts
We know that the flight load acceleration limits with Flaps 39° up to landing weight are 0 to 2.0 G. We can plot these as well.

Because the Vg Diagram should show the aircraft's envelope, we can add the limiting airspeed to the chart.

Landing  Determine Corner Speed (VA)
VA maneuvering speed is where the maximum stall speed intersects with the maximum load factor. Graphically, it occurs in the top left corner, the reason some call this "corner speed.
The G450 published VA of 206 KCAS is much higher than the true VA for a G450 in landing configuration at 50,000 lbs gross weight and 1,000 feet pressure altitude. Full control deflection at 206 knots in this situation could very well overstress the aircraft.
The G450 published VA of 206 KCAS is much higher than the true VA for a G450 in landing configuration at 50,000 lbs gross weight and 1,000 feet pressure altitude. Full control deflection at 206 knots in this situation could very well overstress the aircraft.
Takeoff  Stall Charts
Using the chart provided by Gulfstream, we see the flaps 20° stall speed at 74,600 lbs and 1,000 feet pressure altitude is 132 KCAS.
G450 Stall Speed, Idle Power, Speed Brakes Retracted, Flaps 20°
Takeoff  Derive Range of Stall Speeds for GEnvelope
Recall that
VS=VS(1G)√G We can use that formula to derive a range of stall speeds for varying G loads: G VS 0 0 0.5 93 1.0 132 1.5 162 2.0 187 
We know from G450 Limitations the flight load acceleration limits with Flaps 20° are 0 to 2.0 G.
Takeoff  Determine Corner Speed (VA) Just as we did for the landing example, we can plot the GLimits, airspeed limits, and find the corner speed. In this case, VA = 187 KCAS, still much lower than the published number of 206 KCAS. 
Climb  Stall Charts
Using the chart provided by Gulfstream, we see the flaps 0° stall speed at 70,000 lbs and 3,000' pressure altitude is 130 KCAS.
Using the chart provided by Gulfstream, we see the flaps 0° stall speed at 70,000 lbs and 3,000' pressure altitude is 130 KCAS.
Climb  Derive Range of Stall Speeds for GEnvelope
Climb  Add GLimts
We know from G450 Limitations the flight load acceleration limits with Flaps 0° are 1.0 to 2.5 G.
Climb  Determine Corner Speed (VA)
Now we finally see a VA that equals the published number of 206 KCAS. This isn't the only one, there are many combinations of weight and pressure altitudes that will yield this number.
We know from G450 Limitations the flight load acceleration limits with Flaps 0° are 1.0 to 2.5 G.
Climb  Determine Corner Speed (VA)
Now we finally see a VA that equals the published number of 206 KCAS. This isn't the only one, there are many combinations of weight and pressure altitudes that will yield this number.
G450 VA
Gulfstream G450 Maneuvering Speed (Sea Level)
Gear Flaps Weight VA
Down 39 50,000 lbs 139 knots
Up 20 74,600 lbs 187 knots
Up Up 70,000 lbs 206 knots
As we can see, the published VA is rarely right. Do you need to memorize an continuum of VA's? No, not at all. Maneuvering speed is a certification issue. When controlling your aircraft, do so with a gentle hand and you can avoid overstressing or stalling without the benefit of this made up number. The next time a simulator instructor recommends you fly this speed and the maneuver as required, nod politely and ignore the suggestion.
Gulfstream G450 Maneuvering Speed (Sea Level)
Gear Flaps Weight VA
Down 39 50,000 lbs 139 knots
Up 20 74,600 lbs 187 knots
Up Up 70,000 lbs 206 knots
As we can see, the published VA is rarely right. Do you need to memorize an continuum of VA's? No, not at all. Maneuvering speed is a certification issue. When controlling your aircraft, do so with a gentle hand and you can avoid overstressing or stalling without the benefit of this made up number. The next time a simulator instructor recommends you fly this speed and the maneuver as required, nod politely and ignore the suggestion.