When considering low speed flight, a pilot needs to think more than about stalls, spins, high lift devices, and ground effect. The region of reversed command is far more likely to bite you when you least expect it. No, this isn't a reference to some hokey British flight flick about approaching the speed of sound, this is something that can happen to you in holding, during a climb, or even during an ocean crossing.
We operate at low speeds, intentionally, at least twice every flight, at the start and at the end of each excursion into our rarified existences. For those times and for the other times where the angle of attack is lower than we had intended, having a good understanding of the low speed flight regime is vital.
Oh yes, most of this comes from my notes from freshman aero at Purdue but I did lean heavily on the references listed at the bottom of the page.
We tend to think of the stall as the point the wing simply runs out of speed and the nose drops predictably to prompt us to recover. But is that really what happens? The FAA, [14 CFR 25.103 (a)], defines stall speed thusly:
|Where||VSR||=||Reference stall speed|
|VCLMAX||=||Calibrated airspeed when the load factor-corrected lift coefficient is first a maximum.|
|nZW||=||Load factor normal to the flight path at VCLMAX.|
And the regulation goes on to stipulate: "In addition, when the maneuver is limited by a device that abruptly pushes the nose down at a selected angle of attack (e.g., a stick pusher), VCLMAX may not be less than the speed existing at the instant the device operates."
All of that reinforces with us as we train in simulators that the wing stops producing lift at stall warning and if we don't do anything about it, the nose is going to drop of its own accord, stick pusher notwithstanding. But this clearly isn't true for a swept wing aircraft, where the wing continues to produce lift well beyond CCLMAX as shown by the coefficient of lift graph. The T-38 I flew years ago did not have a stick pusher and when it stalled, the nose didn't pitch at all. (Your only indication was wing buffet and a plummeting VVI.)
In fact, a swept wing, T-tail airplane actually pitches up during the stall. (More on this at Abnormals: Stalls.)
And all of this is the reason most modern swept wing, T-tailed jet aircraft are equipped with stick pushers: to make sure the angle of attack is reduced at or prior to CLMAX to give you an added margin over the aerodynamic stall. From this you may wish to take away a few points:
The first requirement for a spin is to be at or near an aerodynamic stall, the second requirement is for yaw. As we saw in How Wing Shape Affects Stall Warning and Roll Control, a stall begins at the roots for straight wing aircraft and at the tips for swept wing aircraft.
That means a straight wing aircraft has lots of warning that a stall is about to occur and continued aileron control to keep the aircraft in coordinated flight.
Conversely, a swept wing aircraft has less warning and once a stall is reached, less lateral control. A spin is more likely in a swept wing aircraft.
As we saw in the previous discussion about stalls, a swept wing, T-tail aircraft actually pitches up during a stall, making spin entry even more likely if the angle of attack isn't reduced immediately.
Figure: Spin Characteristics, from [Hurt, pg. 310].
The accompanying chart on top is for a straight wing aircraft ("conventional configuration"), and on bottom is for a swept wing aircraft ("high speed configuration").
[Dole, pg. 149] The straight wing aircraft's spin is characterized primarily by the rolling motion with moderate yaw. The attitude of the spin is about 40° or more, nose down. In a straight wing aircraft, a stalled condition must exist before a spin can develop, but this is not true for a swept wing aircraft.
The swept wing aircraft has CL and CD curves as shown [in the figure]. Note that the CL does not have a well-defined maximum lift point. When this type of aircraft is rolled at high angles of attack, only small changes in CL take place. There is no definite stall, and the wing autorotation contribution will be quite weak. The change in CD that occurs between the two wings, however, is substantial and a strong yawing moment is developed.
Modern, low aspect ratio, swept wing aircraft have the mass of the aircraft distributed along the longitudinal axis of the plane rather than in the wings. As the yaw develops, during the spin, this mass contributes to the inertial moments and tends to flatten the spin. This results in extremely high angles of attack and high sink rates.
To get out of a spin you must stop the rotation and lower the angle of attack. The problem in a straight wing aircraft is that your rudder and ailerons may be ineffective during the spin itself. The problem in a swept wing aircraft is that the gyrations may be so extreme that you may not have the time or ability to manipulate the controls quickly enough.
The U.S. Air Force once required all its pilots be well versed in spins and required its pilots master the "Single Spin Recovery" in the T-37:
The procedure is called the "Single Spin Recovery" because, in theory, it will get you out of any spin. We heard war stories of F-4 fighters and large bombers using the procedure to success.
Video: T-37 Spins.
Figure: Flap Configurations, from [Hurt, pg. 40].
We can increase the coefficient of lift of a wing by increasing its camber, decreasing the boundary layer separation, or by adding to the kinetic energy of the airflow above the wing:
For the purpose of this discussion, it will suffice to say these high lift devices serve to replace the existing coefficient of lift curves. In the case of trailing edge flaps, the new curves tend to the higher and displaced to the left, to lower angles of attack. To the pilot this means the angle of attack required for any given amount of lift is reduced.
Figure: Ground Effect, from [Hurt, pg. 380].
As we saw in our discussion about Induced Drag, high pressure from the bottom of the wing spills over to the top from wing tip vortices. Because the aircraft is moving forward, this air spirals downward to depress the down wash of the wing and pulls the aerodynamic force of the wing aft. The aft component of aerodynamic force is induced drag.
The vortices spiral into a growing circle until they hit the fuselage, at which point they end. That is one-half of the wing span. So too, the vortices end as the aircraft nears the runway or any other ground or water surface. When this happens the deflection of the down wash decreases and therefore so does the induced drag.
A similar thing happens to the horizontal stabilizer on low tailed aircraft. As the tail enters ground effect it becomes more effective and may cause a nose-down pitching moment.
When the aircraft is first rotated the wings are in ground effect. As the aircraft climbs to one-half the wing span, some aircraft may have a tendency to settle until more speed is developed. We could definitely notice this on older KC-135A aircraft at heavy weights. The tail can create a nose-up pitching moment when leaving ground effect. On lower power aircraft this can require the odd nose forward pitch input as the aircraft settles. On higher powered aircraft, such as the Boeing 747 or just about any Gulfstream, I've never noticed either issue on takeoff.
For more about this: Basic Aerodynamics / Ground Effect.
When the aircraft enters ground effect during landing, the decrease in induced drag means more of the aerodynamic force is directed parallel to the relative wind. The wing becomes more efficient and the aircraft may have a tendency to float. We noticed this in the Boeing 747, hence the need to "fly the airplane onto the runway" and the warning not to attempt to flare the aircraft to zero sink. A low tailed airplane may also experience a nose-down pitching moment.
Figure: Region of Reversed Command 1, from [Hurt, pg. 354].
As we've seen from our discussions about thrust required curves and L/DMAX, you can plot the thrust required to keep the airplane in unaccelerated flight versus velocity. Where this chart dips and is at a minimum, the lift to drag ratio is at a minimum. At this point drag is at a minimum and the aircraft is flying at its best endurance angle of attack.
Using the first chart as an example, you can see that at Point 2 the airplane is in what an aeronautical engineer calls the region of normal command and at the "available power setting." If you were operating at any point between the bottom of the curve and this point, you would notice the following:
In other words, the thrust relationship to velocity is as you would expect it to be. In should be intuitively obvious to any pilot should always want the airplane in this region.
Notice, however, that Point 1 requires the same thrust but is valid for a lower velocity. This is the region of reversed command, the airplane flies just fine in this region, but your actions are different and your margin for error is smaller.
Figure: Region of Reversed Command 2, from [Hurt, pg. 354].
It might seem an unlikely place to be, but you can find yourself there in several situations, here are two for example.
Portions of this page can be found in the book Flight Lessons 1: Basic Flight, Chapters 15 and 16.
14 CFR 25, Title 14: Aeronautics and Space, Federal Aviation Administration, Department of Transportation
Air Training Command Manual 51-3, Aerodynamics for Pilots, 15 November 1963
Connolly, Thomas F., Dommasch, Daniel 0., and Sheryby, Sydney S., Airplane Aerodynamics, Pitman Publishing Corporation, New York, NY, 1951.
Davies, D. P., Handling the Big Jets, Civil Aviation Authority, Kingsway, London, 1985.
Dole, Charles E., Flight Theory and Aerodynamics, 1981, John Wiley & Sons, Inc, New York, NY, 1981.
FAA-H-8083-15, Instrument Flying Handbook, U.S. Department of Transportation, Flight Standards Service, 2001.
Gulfstream G450 Airplane Flight Manual, Revision 35, April 18, 2013.
Gulfstream G450 Aircraft Operating Manual, Revision 35, April 30, 2013.
Hage, Robert E. and Perkins, Courtland D., Airplane Peformance Stability and Control, John Wiley & Sons, Inc., 1949.
Hurt, H. H., Jr., Aerodynamics for Naval Aviators, Skyhorse Publishing, Inc., New York NY, 2012.
Technical Order 1T-38A-1, T-38A/B Flight Manual, USAF Series, 1 July 1978.