# Wind Tunnel

Aeroelasticity.

1

Although we like to think of our airplanes as strong, rigid structures, nothing is perfectly rigid. All real physical objects are somewhat flexible and will distort when loaded, including airplanes.

An airplane in flight changes shape in response to the forces acting on it. These shape changes affect the aerodynamic characteristics of the airplane and change the forces. This coupling between the aerodynamics of the airplane and its structural shape is called aeroelasticity.

Modern sailplane wings are extremely flexible and change shape significantly when loaded. New shapes mean new aerodynamics—which must be accounted for in design.

Static and Dynamic Effects

There are two general classes of aeroelastic phenomena. In the first, called “static,” the airplane changes shape in response to aerodynamic forces. This shape change affects the aerodynamics of the airplane, changing its characteristics from what one would expect if the airplane were truly rigid. In the static case, the shape of the airplane reaches equilibrium in response to an applied aerodynamic force, and the airplane reaches a steady-state, albeit distorted shape, once equilibrium is established.

In the dynamic case, the airplane, or part of it, is oscillating, usually both bending and twisting. This gives rise to varying aerodynamic forces that can either drive or damp the structural oscillation. If the aeroelastic oscillations become unstable, the results can be catastrophic.

This month we will begin a look at static aeroelastic phenomena.

Wing Bending

The simplest form of aeroelastic deflection is wing bending. The wing generates the lift that holds the airplane in the air. The lift force is distributed along the span of the wing, while most of the weight of the airplane is concentrated in the fuselage. Because of this, the lift causes the wing to bend upwards along its length. The more lift that is being generated, the more the wing bends.

You can see this effect clearly during the take off of an airliner. When the airplane rotates for liftoff, the wing tips rise quite significantly relative to the fuselage before the wheels leave the ground. In flight, the wings have noticeably more dihedral than they do when the airplane is static on the ground. Another good example is the wings of high performance sailplanes, which due to their very high aspect ratio, are quite flexible.

Once the airplane is in flight, the wing bends to its 1-G shape, the shape the wing takes on when supporting the weight of the airplane in steady-state, level flight. Any change in the load factor (G-loading) changes the amount the wing bends. In a turn or pull-up, where the load factor is greater than one, the wing will bend more, and if the wing is unloaded by a pushover or down-gust, it will bend less.

The aeroelastic bending of the wings has multiple effects on the airplane. One potentially beneficial effect is that the flexing of the wing acts somewhat like the springs in an automotive suspension. When the airplane encounters a gust and the lift of the wing increases, the first effect of the increased lift is to bend the wing. The flexible wing transmits the load increment caused by the gust to the fuselage more gradually than a rigid wing. This reduces the onset rate of the gust loading and softens the ride, reducing the peak loads experienced by the passengers and other items in the fuselage. If the wing is very flexible, wing bending can increase the dihedral sufficiently to slightly reduce the total lift the wing is producing, further reducing the G-onset rate at the fuselage.

In extreme cases this “shock absorber” phenomenon can cause some issues with cues to the pilot. If the pilot pulls back on the stick to initiate a pull-up, the wing bending will reduce the onset rate of the commanded G-load at the cockpit. The pilot may interpret this as a lag in the control response of the airplane, and respond by pulling harder, just as the initially commanded G is finally felt in the cockpit. This has the potential to lead to PIO (Pilot Induced Oscillation) or overstressing the airplane due to the pilot’s attempts to compensate for the perceived lag in control response. Fortunately, this situation is rare, and only seen on very extreme designs.

Wing bending in flight also affects the lateral/directional characteristics of the aircraft. As the wings bend upwards in response to lift loads, their dihedral increases. The dihedral increase changes the characteristics of the airplane. It has its largest effect on the Dutch roll mode. The designer must take this into account and choose the static dihedral angle and fin size to ensure that the airplane has acceptable Dutch roll damping when flying in its true, deflected shape.

This task is complicated somewhat by the fact that the physical dihedral will increase with load factor, so that the airplane will have more dihedral when maneuvering than it does when flying straight and level. It is quite possible that the flight condition that sizes the vertical fin for a relatively flexible airplane will be a maneuvering condition, rather than steady, level flight.

If the wing is very flexible, wing bending can move the vertical position of the aerodynamic center far enough, or change the vertical position of wing-mounted control surfaces or masses enough, to affect the longitudinal characteristics of the airplane. This is very rare, since few airplanes are flexible enough for the longitudinal effects of wing bending to be significant. Unfortunately, it is not unheard of. The destruction of the Helios ultra-high-altitude flying wing UAV was caused in part by longitudinal effects of wing bending. During a test flight, Helios encountered turbulence that caused the wing to go into what the accident report called “an unexpected persistent high-wing-dihedral configuration.” The airplane was longitudinally unstable in this configuration and began a series of pitch oscillations that led to it eventually exceeding its maximum allowable airspeed and breaking up.

NASA’s solar-powered Helios flying wing, shown here on its first test flight on solar power, had a very flexible wing which achieved significant shape changes under load.

Wing flexibility can also sometimes cause issues on the ground. A few airplanes, like the B-52 and B-47, have auxiliary or “outrigger” landing gear to stabilize them and support large, flexible wings when the airplane is on the ground.

As we saw earlier, aeroelastic wing bending can happen before the wheels leave the ground. On airliners, this effect is benign. The wings gradually flex upward towards their 1-G shape during the takeoff. On occasion, aeroelastic wing bending on the ground can cause significant problems.

The most well known incident of this type was the takeoff of the Voyager on its unrefueled around-the-world flight. Before the takeoff for the world-circling flight, there was considerable concern about the dangers of the heavily loaded airplane lifting off prematurely. To prevent this, the landing gear was adjusted to place the airplane slightly nose-down so that it would require a positive nose-up control input from pilot Dick Rutan to lift off. During the takeoff roll, the nose-down attitude caused the wings, which were heavily loaded with fuel and drooping significantly under the weight, to develop negative lift that flexed the wing tips down so far that they dragged on the runway. Fortunately, although the damage done to the tips caused the airplane to lose both winglets, it was still able to complete the flight successfully.

In-flight wing bending can affect the function, and hence design of airplane subsystems that are in or on the wings. The design of control surfaces and fuel systems require particular attention to the geometric effects of wing bending.

The Helios became a victim of pitch oscillations that began with high wing dihedral due to structural flexibility. It came apart in mid-air­—but fortunately it was over the ocean and unmanned.

Fuel System

If the wing is flexible enough to change its dihedral significantly in flight, then the vertical position of fuel in tanks inside the wing will be a function of the wing deflection. On the ground, the wing will droop under the weight of the fuel, and the fuel will tend to pool towards the wing tips. If the fuel tank vents are near the tips, this droop can cause fuel to leak out of the vents. One solution to this that has appeared on several airplanes is to incorporate small winglets that are tall enough so that the tip of the winglet is above the top of the fuel tanks when the wing is in its most drooped condition. The fuel vent line runs out the top of the winglet, ensuring that the vent opening remains above the level of the fuel, thus preventing leakage.

The movement of the fuel due to wing bending can also cause problems with the location of the fuel line pickup. In flight, with the wings bent upwards, the fuel moves inboard, and will pool in the inboard part of the tanks when the tanks are partially full. This suggests that the proper place for the fuel line to pick up fuel is inboard. On the ground, wing droop can cause the fuel to move outboard, which introduces the danger that an inboard fuel pickup may unport and suck air on the ground with partially-filled tanks. The design of the fuel system must take both of these situations into account.

Controls

The control linkages that actuate the ailerons can be significantly affected by wing bending. On typical systems, the stick is connected to the ailerons by either cables or push-pull tubes. Both cables and push-pull linkages run in straight lines between bell cranks or pulleys.

When the wing bends, the path of the control linkage changes. This can cause cables to overtighten or go slack, and can cause push-pull tubes to bind against structure or generate unwanted control inputs. Linkages running spanwise in flexible wings must be designed with this in mind. On cable systems, additional pulleys or fairleads may be needed to control the effects of bending on the cables. On push-pull systems, it may be necessary to break the control run up into several segments with idlers between them.

Control surface binding can also become an issue. In order for an aileron to move freely about its hinges, the hinge pins must be parallel to each other. If the aileron is mounted on a piano hinge, the hinge must be straight. If the wing bends enough to bend the aileron and significantly misalign the aileron hinges, it will bind. There are several solutions to this problem. The two most common are to use floating hinges, where the hinge pin goes through a ball like the ball used on a rod end, and can change its orientation as the wing bends to relieve the binding. A second approach that is more appropriate for very long, flexible wings is to use several relatively short span ailerons in series along the wing span. Each individual aileron is short enough so that it will not bend enough to bind. This is an effective way of preventing control binding, but does make the aileron control linkages more complex.

Bending of the wing is the simplest aeroelastic phenomenon a designer must consider. Next month we will continue our look at aeroelasticity when we consider what happens when air loads twist components of the airplane.

Photos: Larry Pardue, courtesy NASA

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Barnaby is a Technical Fellow for Northrop Grumman’s Advanced Design organization. A private pilot with single-engine and glider ratings, Barnaby has been involved in the design of unconventional airplanes including canards, joined wings, flying wings and some too strange to fall into any known category.

#### 1 COMMENT

1. Mr. Wainfan cites sailplanes as examples of the lean, limber structures most prone to flutter, but omits them when it comes to how one might address control surface binding under deflection. The most common solution for composite sailplanes is simply to tailor the flap and aileron structures to maximize torsional stiffness while minimizing bending stiffness, even to in-plane bending that stretches or shrinks the spanwise lengths of the leading and trailing edges. Oh, and also have lots of hinge points. The result is a long, narrow surface that deflects easily even when the path through the hinge points is curved. On my HP-24 sailplane flaperons, I use lightweight sandwich skins with a single ply of 2 oz Kevlar on each side of 3mm PVC foam. All of the fibers in the structure are +/-45, and the closure joint at the trailing is carefully designed to minimize the bondline thickness. I modeled this construction on the flaps of Gerhard Waibel’s ASW flaperons.

–Bob Kuykendall

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