128 Sentences With "yawing" | Random Sentence Generator

This function apparently gives you better control when pitching, rolling, and yawing.

There was a yawing hole in the pub that couldn't quite be filled.

When it gets up from its charging base it makes an odd, child-like yawing sound.

A ship's constant yawing, pitching and rolling disturbs the powder before the beam can do its work.

Soon the water was blue and deep, and our ship was pitching and yawing with the slightest surf.

The mission goes as planned until the rocket-propelled NF-2104A reaches 256,20760 feet and goes into an uncontrollable yawing and rolling motion.

But as it has been for 90 prior parades, it was also thronged by children, packed with marching bands and dotted overhead with leviathan balloons yawing in blue-sky breeze.

MOGADISHU, Somalia (Reuters) - A collection of yawing mouths and extracted teeth, booming stereo speakers and colorful hookah pipes adorn shop fronts in Somalia, a colorful contrast to the airbrushed artworks of big business.

Moored along a four-block stretch of shore where the Hudson meets Manhattan are turbocharged tour boats painted green with gaping jaws, hulking ferries, yawing cruise ships, idling tugboats and a conga line of sightseeing craft picking up tourists.

The AR-15, like the M4 and M16 rifles issued to American soldiers, shoots lightweight, high-speed bullets that can cause grievous bone and soft tissue wounds, in part by turning sideways, or "yawing," when they hit a person.

So in a flight sim or space game you could be looking around the cockpit or directing the guns with the mouse itself, yawing and rolling with the full-mouse joystick and controlling thrust and strafing with the little joystick.

Directly afterwards the French frigate ran up on our larboard and lee quarter, and yawing rapidly, fired into us.

Roll rate generates fin lift causing a yawing moment and also differentially alters the lift on the wings, thus affecting the induced drag contribution of each wing, causing a (small) yawing moment contribution. Positive roll generally causes positive N_p values unless the empennage is anhedral or fin is below the roll axis. Lateral force components resulting from dihedral or anhedral wing lift differences has little effect on N_p because the wing axis is normally closely aligned with the center of gravity. :::N_r Yawing moment due to yaw rate.

Victoria and Walter with their configuration and acquired the nickname "Boxers" for the typical yawing motion of type. Trials in 1837 revealed that Walter was more powerful than Royal William. Both were converted to tender locomotives, possibly in an effort to reduce the yawing. They were painted green, acquiring the numbers five and six respectively and possibly losing their names from the 1840s.

9 These "high-speed stalls" produce the same buffeting characteristics as 1g stalls and can also initiate a spin if there is also any yawing.

A400M, counter-rotating propellers on each wing; the most important yawing moments after failure of engine 1 If an outboard engine fails, such as engine 1 as shown in Figure 2, the moment arm of the vector of the remaining thrust on that wing moves from in between the engines to a bit outside of the remaining inboard engine. The vector itself is 50% of the opposite thrust vector. The resulting thrust yawing moment is much smaller in this case than for conventional propeller rotation. The maximum rudder yawing moment to counteract the asymmetrical thrust can be smaller and, consequently, the size of the vertical tail can be smaller.

It is also known as a "tailslide", from the yawing turn, which is different from the typical method of turning an aircraft in the pitch axis.

The remaining engine's asymmetrical thrust would cause the aircraft to yaw violently to one side. SAS, autopilot, and manual control inputs would fight the yawing, but often the extreme off-angle would reduce airflow in the opposite engine and stimulate "sympathetic stalls". This generated a rapid counter-yawing, often coupled with loud "banging" noises, and a rough ride during which crews' helmets would sometimes strike their cockpit canopies.Crickmore 1997, pp. 42–43.

Any factor that has influence on the balance of forces and on the yawing and rolling moments after engine failure might also affect VMCs. When the vertical tail is designed and the VMCA is measured, the worst-case scenario for all factors is taken into account. This ensures that the VMCs published in the AFMs guaranteed to be safe. Heavier aircraft are more stable and more resistant to yawing moments, and therefore have lower VMCAs.

VPPs solve for the performance of a yacht by resolving all forces and moments acting on the yacht. Pitching and yawing moments can be assumed to be zero for simplicity.

Yaw is induced by a moveable rudder-fin. The movement of the rudder changes the size and orientation of the force the vertical surface produces. Since the force is created at a distance behind the centre of gravity, this sideways force causes a yawing moment then a yawing motion. On a large aircraft there may be several independent rudders on the single fin for both safety and to control the inter-linked yaw and roll actions.

Testing was initiated on January 7, 1968 and ended one month later on February 7. It was quickly determined that the cause of the divergence was the Styrofoam cockpit enclosure. As the vehicle's sideslip angle reached minus two degrees, a yawing force rapidly built up that exceeded the ability of the yaw thrusters to counteract. The fix decided on was simply to remove the top of the enclosure, thus venting it and eliminating the excessive yawing force.

Directional or weathercock stability is concerned with the static stability of the airplane about the z axis. Just as in the case of longitudinal stability it is desirable that the aircraft should tend to return to an equilibrium condition when subjected to some form of yawing disturbance. For this the slope of the yawing moment curve must be positive. An airplane possessing this mode of stability will always point towards the relative wind, hence the name weathercock stability.

Yaw rate input at any roll angle generates rudder, fin and fuselage force vectors which dominate the resultant yawing moment. Yawing also increases the speed of the outboard wing whilst slowing down the inboard wing, with corresponding changes in drag causing a (small) opposing yaw moment. N_r opposes the inherent directional stiffness which tends to point the aircraft's nose back into the wind and always matches the sign of the yaw rate input. :::L_\beta Rolling moment due to sideslip.

A special form of asymmetric stall in which the aircraft also rotates about its yaw axis is called a spin. A spin can occur if an aircraft is stalled and there is an asymmetric yawing moment applied to it.FAA Airplane flying handbook Chapter 4, pp. 12–16 This yawing moment can be aerodynamic (sideslip angle, rudder, adverse yaw from the ailerons), thrust related (p-factor, one engine inoperative on a multi-engine non-centreline thrust aircraft), or from less likely sources such as severe turbulence.

The Magnus effect can also be found in advanced external ballistics. First, a spinning bullet in flight is often subject to a crosswind, which can be simplified as blowing from either the left or the right. In addition to this, even in completely calm air a bullet experiences a small sideways wind component due to its yawing motion. This yawing motion along the bullet's flight path means that the nose of the bullet points in a slightly different direction from the direction the bullet travels.

A rear tire blowout will cause the vehicle to become very difficult to control, especially at highway speeds. It also greatly increases the risk of rollover due to yawing, a condition where the rear of the vehicle swings out and becomes perpendicular to the direction of travel: yawing can cause the tire to separate from the rim, leading the rim to dig into the pavement, or dirt and grass if no longer on the road, which can trip the vehicle and cause its rollover.

The critical engine of a multi-engine fixed-wing aircraft is the engine that, in the event of failure, would most adversely affect the performance or handling abilities of an aircraft. On propeller aircraft, there is a difference in the remaining yawing moments after failure of the left or the right (outboard) engine when all propellers rotate in the same direction due to the P-factor. On turbojet and turbofan aircraft, there usually is no difference between the yawing moments after failure of a left or right engine.

When one engine fails, a yawing moment develops, which applies a rotational force to the aircraft that tends to turn it toward the wing that carries the engine that failed. A rolling moment might develop, due to the asymmetry of the lift in each wing, with a greater lift generated by the wing with the operating engine. The yawing and rolling moments apply rotational forces that tend to yaw and roll the aircraft towards the failed engine. This tendency is counteracted by the pilot's use of the flight controls, which include the rudder and ailerons.

The most important forces and moments acting on the aircraft while using the rudder to counteract the asymmetrical thrust and while keeping the wings level. Notice a sideslip cannot be avoided for when the yawing moment is being counteracted.When an engine on a multi-engine aircraft fails, the thrust distribution on the aircraft becomes asymmetrical, resulting in a yawing moment in the direction of the failed engine. A sideslip develops, causing the total drag of the aircraft to increase considerably, resulting in a drop in the aircraft's rate of climb.

Alternatively, positive angle of attack must generate positive yawing moment on a statically stable missile, i.e. N_\beta must be positive. It is common practice to design manoeuvrable missiles with near zero static margin (i.e. neutral static stability).

Mason 1992, p. 339. On the initial flight, an uncontrollable yawing motion was discovered, which led to a redesigned larger rudder; however, no difficulties had been attributed to the groundbreaking turbojet propulsion.Butler and Buttler 2006, p. 15.Shacklady 1962, p. 21.

Norris and Wagner, Boeing Upon missile detonation, the jumbo jet began to experience oscillations (yawing) as the dual channel yaw damper was damaged. Yawing would not have occurred if hydraulic systems one or two were fully operational. The result is that the control column did not thrust forward upon impact (it should have done so as the plane was on autopilot) to bring down the plane to its former altitude of . This failure of the autopilot to correct the rise in altitude indicates that hydraulic system number three, which operates the autopilot actuator, a system controlling the plane's elevators, was damaged or out.

Almost immediately after separation of the stabilizer, the aircraft began to exhibit Dutch roll, simultaneously yawing right and banking right, before yawing back left and banking left. At some points during the flight, the banking motion became very profound, with the banks in large arcs of approximately 50° back and forth in cycles of 12 seconds. Despite the complete loss of controls, the pilots continued to turn the control wheel, pull on the control column, and move the rudder pedals up until the moment of the crash. The pilots also began efforts to establish control using engine thrust, as the aircraft slowly wandered back towards Haneda.

The rudder, and to a certain extent the ailerons via the use of bank angle, are the only aerodynamic controls available to the pilot to counteract the asymmetrical thrust yawing moment. The higher the speed of the aircraft, the easier it is to counteract the yawing moment using the aircraft's controls. The minimum control speed is the airspeed below which the force the rudder or ailerons can apply to the aircraft is not large enough to counteract the asymmetrical thrust at a maximum power setting. Above this speed it should be possible to maintain control of the aircraft and maintain straight flight with asymmetrical thrust.

Particularly at low-to-medium wind speeds, yawing can make a significant reduction in turbine output, with wind direction variations of ±30° being quite common and long response times of the turbines to changes in wind direction. At high wind speeds, the wind direction is less variable.

The Washington Post, 13 December 1964: G1.Fonda: A person of many parts: A restless yawing between extremes By Martin Kasindorf. New York Times, 3 February 1974: 228. Catherine Spaak later claimed that Vadim was focused on Fonda during the making of the film so "everyone suffered".

It can also be tilted in any direction and fully rotated. Sphere-and- ring boards provide the greatest freedom of movement of any type of balance board, allowing rotation about all axes (yawing, pitching and banking) and translation (i.e., sliding) in both transverse (i.e., lateral) and longitudinal directions.

A yaw damper (sometimes referred to as a stability augmentation system) is a system used to reduce (or damp) the undesirable tendencies of an aircraft to oscillate in a repetitive rolling and yawing motion, a phenomenon known as the Dutch roll. A large number of modern aircraft, both jet-powered and propeller- driven, have been furnished with such systems. The use of a yaw damper provides superior ride quality by automatically preventing uncomfortable yawing and rolling oscillations and reduces pilot workload. On some aircraft, it is mandatory for the yaw damper to be operational at all times during flight above a specified altitude; several airliners were deemed to be unsafe to fly without an active yaw damper.

Therefore, friction coefficients of all parts involved in force transmission also play a major role in system design. Also, close attention has to be paid to the ratio of the moment of inertia of the robot body and its ball in order to prevent undesired ball spin, especially while yawing.

Another issue with the P-38 arose from its unique design feature of outwardly rotating (at the "tops" of the propeller arcs) counter-rotating propellers. Losing one of two engines in any twin-engine non- centerline thrust aircraft on takeoff creates sudden drag, yawing the nose toward the dead engine and rolling the wingtip down on the side of the dead engine. Normal training in flying twin-engine aircraft when losing an engine on takeoff is to push the remaining engine to full throttle to maintain airspeed; if a pilot did that in the P-38, regardless of which engine had failed, the resulting engine torque and p-factor force produced a sudden uncontrollable yawing roll, and the aircraft would flip over and hit the ground.

A piston pump has a very light suction phase, but the upstroke is heavy and puts a big backtorque on a starting rotor when the crank is horizontal and ascending. A counterweight on the crank up in the tower and yawing with the wind direction can at least spread the torque to the crank descent.

The aircraft lacks a tail rotor, as the coaxial, contra-rotating main rotors produce zero net torque. Yawing motion is produced and controlled by electronic gyroscopically-controlled differential electric braking of the main rotors. With its empty weight of and a gross weight of the H-4 has a useful load of . With full fuel of the payload is .

Using the ailerons to roll an aircraft to the right produces a yawing motion to the left. As the aircraft rolls, adverse yaw is caused partly by the change in drag between the left and right wing. The rising wing generates increased lift, which causes increased induced drag. The descending wing generates reduced lift, which causes reduced induced drag.

One response to a single unstart was unstarting both inlets to prevent yawing, then restarting them both.Landis and Jenkins 2005, p. 97. After wind tunnel testing and computer modeling by NASA Dryden test center, Lockheed installed an electronic control to detect unstart conditions and perform this reset action without pilot intervention.Rich and Janos 1994, p. 221.

When the Range-Doppler plane and the coordinate plane are different, the ISAR image can not reflect the real shape of the target. Thus, the ISAR imaging can not obtain the real shape information of the target in most situations. Rolling is side to side. Pitching is forward and backwards, yawing is turning left or right.

A lever essential to the experiment broke off when pulled. The second involved the photographic coverage objective. It was only partially successful due to an improper lens setting on the 16 mm camera. Early in the flight, the crew noticed the craft gradually yawing left: > 00 18 41 (Command Pilot) I seem to have a leak.

Due to P-factor, a clockwise rotating right-hand propeller on the right wing typically develops its resultant thrust vector at a greater lateral distance from the aircraft's center of gravity than the clockwise rotating left-hand propeller (Figure 1). The failure of the left-hand engine will result in a larger yawing moment by the operating right-hand engine, rather than vice versa. Since the operating right-hand engine produces a larger yawing moment, the pilot will need to use larger deflections of the flight controls or a higher speed in order to maintain control of the aircraft. Thus, the failure of the left-hand engine has a greater impact than failure of the right-hand engine, and the left-hand engine is called the critical engine.

Rather, the system is intended to counteract incidental and undirected yawing motions, which can be characterised as skids or slips. On a single-engine aircraft, the system is particularly useful at addressing the tendency to 'fishtail', smoothing out the left-right movements of the vertical stabilizer, increasing ride comfort. It is also particularly useful on swept wing aircraft, particularly those using a T-tail arrangement; without an active yaw damper system, these types of aircraft are susceptible to the Dutch roll phenomenon, where yawing motions can result in repetitive corkscrew-like oscillations that could potentially escalate to excessive levels if not effectively counteracted. The yaw damper is typically disengaged at ground level and turned on shortly after takeoff; an active yaw damper during the takeoff run could potentially mask serious issues such as engine failure.

CH-46 Sea Knight Animation Tandem rotor helicopters have two large horizontal rotor assemblies mounted one in front of the other. Currently this configuration is mainly used for large cargo helicopters. Single rotor helicopters need a mechanism to neutralize the yawing movement produced by the single large rotor. This is commonly accomplished by a tail rotor, coaxial rotors, and the NOTAR systems.

When an unstart occurred on the SR-71 very large drag from the unstarted nacelle caused extreme rolling/yawing. The aircraft had an automatic restart procedure which balanced the drag by unstarting the other intake. This intake had its own tremendous drag with the spike fully forward to capture the shock wave in front of the intake."Flying the SR-71 Blackbird" Col.

If the wing has dihedral, this will result in a side force momentarily opposing the resultant sideslip tendency. Anhedral wing and or stabilizer configurations can cause the sign of the side force to invert if the fin effect is swamped. :::Y_r Side force due to yaw rate. Yawing generates side forces due to incidence at the rudder, fin and fuselage.

"Lateral-directional" modes involve rolling motions and yawing motions. Motions in one of these axes almost always couples into the other so the modes are generally discussed as the "lateral-directional modes"."Lateral" is used although the rolling motions are about the longitudinal axis There are three types of possible lateral-directional dynamic motion: roll subsidence mode, spiral mode, and Dutch roll mode.

This set the no. 1 engine on fire. Accident investigators presumed that this engine stopped producing power after only 30 seconds of flight. The flightdeck crew did not feather the engine's propeller as the aircraft was still slowly climbing to 700–800 feet above mean sea level (amsl)/300–400 ft above ground level (agl), with a "crabbing" or "yawing" motion to the left.

The aircraft had a large cruciform stabilizer in order to improve directional stability for low-level flight. Split ailerons were fitted that could be used as airbrakes. When these airbrakes were operated asymmetrically in conjunction with the aircraft's rudder, sideways control forces could be applied (and the aircraft moved sideways) without yawing or banking, easing weapon aiming.Fink Aviation Week & Space Technology October 2, 1972, pp. 45–46.

Warping the wing did what was expected in terms of lift, thereby rolling the plane, but also had an effect on drag. The result was that the upward-moving wing was dragged backwards, yawing the glider. If this yaw was violent enough, the additional speed on the lower wing as it was driven forward would make it generate more lift, and reverse the direction of the roll.

Penguin had the weather gage and for a time, Hornet ran before Penguin, yawing occasionally to avoid being raked. Then Penguin turned up-wind to port at almost the same moment as Hornet turned to starboard. The two vessels exchanged broadsides for 15 minutes, with the range gradually closing from "musket shot". Dickenson turned downwind, to close with Hornet in an attempt to board and capture Hornet, but was mortally wounded.

When aileron control was input, they were deflected up or down as a single unit, just like an aileron. When rudder input was made, the two surfaces on one side opened, top and bottom, creating drag, and yawing the aircraft. By applying input to both rudder pedals, both sets of surfaces were deployed creating drag so that the airspeed or the glide angle could be manipulated.Winchester 2005, p. 193.

These reversed the layout, placing the cylinders inside, between the frames, and below the smokebox at the front. The inside cylinders were closer together, giving less of a rocking couple and so were less prone to yawing oscillation at speed. Placing the cylinders below the smokebox also permitted shorter steampipes and exhaust pipes to the blastpipe, giving better efficiency. Northumbrians were the last, and only, production locomotives with this wheel arrangement.

The Coriolis effect is a concern for pilots, where it can cause extreme disorientation. This happens as pilots accelerate their aircraft and also need to check their instruments, which often involves moving their heads. This is particularly dangerous for an airborne pilot because it give the feeling that they are pitching, yawing, and rolling simultaneously; In extreme situations, this can cause the pilot to lose control of the aircraft.

The As.III offered poor performance above 3,000 m and the D.IIa was mostly relegated to operations on the Eastern Front. Nicknamed Haifisch (shark) for its sleek appearance, the D.II and D.IIa proved generally unpopular in service due to poor fields of view and heavy controls. It was quite fast and strong, but had mediocre manoeuvrability and handling. However, it is also reported that the aircraft had particularly sensitive controls, particularly in the yawing plane.

The position of all three axes, with the right-hand rule for its rotations The yaw axis has its origin at the center of gravity and is directed towards the bottom of the aircraft, perpendicular to the wings and to the fuselage reference line. Motion about this axis is called yaw. A positive yawing motion moves the nose of the aircraft to the right. The rudder is the primary control of yaw.

They are also in a more accessible location for maintenance or replacement. However, disadvantages include a higher risk of the engines ingesting foreign objects as they have a lower ground clearance, and a larger yawing moment during an engine failure. The supersonic airliner Concorde had its engines mounted in rectangular pods conformal to the underside of the wing, without any pylons. The omission of pylons reduces drag and eliminates the risk of them being overstressed.

Bombylius major (commonly named the large bee-fly or the dark-edged bee-fly) is a parasitic bee mimic fly. B. major is the most common type of fly within the Bombylius genus. The fly derives its name from its close resemblance to bumblebees and are often mistaken for them. B. major exhibits a unique flight behavior known as "yawing" and plays a role in general pollination, without preference of flower types.

It has been discovered that the fly is capable of a unique type of flight behavior, which was discovered with the use of a high speed camera. In this behavior, the flies are seen to rotate around a vertical axis as they fly (this action is known as “yawing”). However, it is still unknown what can cause this behavior to be triggered and what purpose it serves, but a proposed explanation includes mating habits.

The first full sized model of these to fly was designated "Prandtl-D No. 3", and flown in a series of tests on October 28, 2015 at the Armstrong Flight Research Center in Edwards, California. The aircraft is centered around the testing of yawing without a vertical stabilizer. The manager of the project, Albion Bowers, said that the aircraft is based on the flight of a bird. The Prandtl-D No. 3 first flew Oct.

The crew did not recall any unusual sink rate, buffeting and yawing, nor were there any instrument warnings except a last-moment flashing of the heading-difference light. The aircraft hit the water with the tail first.National Transportation Safety Board: 20 The impact caused the fuselage to break into three main parts. The largest was the 26-meter (85 ft) forward section of the aircraft, from the nose to the trailing edge of the wings.

One of the Phantoms experienced failure of one engine, and its second engine began to overheat. It was diverted to Gander Airport, Newfoundland, but could not maintain level flight. Crew E-113 managed to connect its boom to the Phantom's refueling receptacle and literally tow the fighter back up to 10,000 feet above sea level. The refueling was further complicated by the partial loss of hydraulics by the fighter, which caused it to fly while yawing.

The rules state that the overspeed margin has increased to 120 percent for one engine under no load, while for operating conditions, the margin is 105 percent. In addition to the overspeed requirements put forth by the FAA, they have also stated new rotor design criteria. Along with overspeed protection by automation controls, there are ways to prevent overspeed by maneuvering controls. Milton D. McLaughlin goes into detail on pitches, yawing, climb outs, and other maneuvering techniques.

The tempest swamped or set adrift numerous boats and landing craft, among them the captain's gig. Kitkun Bay alternatively used both engines that morning to relieve the strain on the anchor chain and to minimize yawing. The wind abated by noon to a comparatively moderate 45 knots. The crew rode out the typhoon and savored their first liberty ashore on the Japanese mainland during the ship's ten-day (17–27 September 1945) stay in the Tōkyō Bay area.

Hence, some people are requesting that this mode of transportation be phased out, which is also blamed as a major source of air pollution in cities. Jeepneys are often mechanically unsound, and not at all roadworthy, with their balding tyres, crabbing and yawing from distorted subframes, with poor emissions. Their longitudinal seating and lack of any seat-belts is less than safe. The low height of the saloon, and the extended roof above the driver, make visibility very poor.

In the mid-1980s, the Federal Aviation Administration grounded the Beechcraft Bonanza due to safety concerns. While the Bonanza met the initial certification requirements, it had a history of fatal mid-air breakups during extreme stress, at a rate exceeding the accepted norm. The type was deemed airworthy and restrictions removed after Beechcraft issued a structural modification as an Airworthiness Directive. V-tailed aircraft require longer rear fuselages than aircraft with conventional empennages to prevent yawing.

During a series of taxi trials the port landing gear collapsed on May 22; the damage was quickly repaired and the first flight was on July 15, 1954. Following flights revealed a propensity to "Dutch roll" - an alternating yawing and rolling motion. Boeing already had experience with this on the B-47 Stratojet and B-52 Stratofortress and had developed a yaw damper system on the B-47 that could be adapted to the Dash 80.

Lockheed test pilot Bill Parks could not overcome the roll. At about a 45-degree bank angle and altitude he ejected and was blown sideways out of the aircraft. Although he was not very high off the ground, his parachute opened and he landed safely. On 28 December 1965, the third A-12 was lost when "Article 126" crashed 30 seconds after takeoff when a series of violent yawing and pitching actions was followed very rapidly with the aircraft becoming uncontrollable.

Its electromechanical yawing, asynchronous generator, and the three stall-regulated blades with emergency aerodynamic tip brakes (these were invented by Juul) is a design that is still widely used in Denmark. Stall control was provided through an asynchronous generator. The turbine, which for many years was the world's largest, operated from 1957 to 1967 without maintenance, demonstrating incredible durability. In connection with NASA testing for the U.S. wind energy programme, it was refurbished in 1975 and brought back into operation.

Both sexes engage in high, circling flight but literature details are sketchy. Soaring activities may primarily be variations on territorial defense flights as opposed to courtship per se. The "flutter-glide" flight consists of a series of shallow, rapid wing beats interspersed with brief glides and may serve to advertise the territory. The "sky-dance" is stimulated by an intruder and consists of slow flight with deep, labored wing beats with irregular yawing and pitching that may terminate in steep dives.

Ohio was sinking not much more than 45 miles west of Malta. Under the protection of the Spitfires, the danger of enemy attacks receded. After the tow line was parted, Ledbury was still secured to Ohio by a heavy wire which had been pulled round by the heavily yawing tanker, and had ended up alongside Penn, facing the wrong way. After a quick analysis of the possibilities, it was decided to tow the tanker with a destroyer on either side of the tanker.

Focke-Wulf Fw 190 A-8 in a ground loop. The right-side main undercarriage is collapsing In aviation, a ground loop is a rapid rotation of a fixed-wing aircraft in the horizontal plane (yawing) while on the ground. Aerodynamic forces may cause the advancing wing to rise, which may then cause the other wingtip to touch the ground. In severe cases (particularly if the ground surface is soft), the inside wing can dig in, causing the aircraft to swing violently or even cartwheel.

If throttle settings allow the throttles to be shifted without affecting the total amount of power, then yaw control can be combined with pitch control. If the aircraft is yawing, then the wing on the outside of this yaw movement will go faster than the inner wing. This creates higher lift on the faster wing, resulting in a rolling movement, which helps to make a turn. Controlling airspeed has been shown to be very difficult with engine control only, often resulting in a fast landing.

This loss of weight, together with President's constant yawing, allowed Belvidera to put so much water between them that President ceased firing. Congress however was still in the chase, overtaking President at 18:30 and opening fire. Finding her shots falling short however, she too stopped firing soon after. Belvidera continued to shed weight, throwing her water and boats over the side in an attempt to put distance between her and her pursuers, and by 20:00, she was two miles ahead of the nearest American ship.

Although usually stable in a normal aircraft, the motion may be so slightly damped that the effect is very unpleasant and undesirable. In swept-back wing aircraft, the Dutch roll is solved by installing a yaw damper, in effect a special-purpose automatic pilot that damps out any yawing oscillation by applying rudder corrections. Some swept-wing aircraft have an unstable Dutch roll. If the Dutch roll is very lightly damped or unstable, the yaw damper becomes a safety requirement, rather than a pilot and passenger convenience.

Stiesdal's initial work in the late 1970s and early 1980s contributed significantly to the development of the simple and robust technologies of the so-called Danish Concept, comprising upwind, automatic yawing and two-speed stall-regulated turbines with fail-safe safety systems.Reve (2011). 2011 Poul la Cour Prize to Siemens’ Henrik Stiesdal – a pioneer of modern wind energy technology Reve - Wind Energy and Electric Vehicle Review, 15 March 2011. This concept is considered as the basis of the dominant position of the Danish wind industry through the following decades.

In the overland attack role this gave the F-14D 60 percent more striking range or one-third more time on station. The rate of climb was increased by 61 percent. The F110's increased thrust allowed almost all carrier launches to be made in military (dry) power. While this did result in fuel savings, the main reason not to use afterburner during carrier launches was that if an engine failed the F110's thrust in full afterburner would produce a yawing moment too abruptly for the pilot to correct.

The task of orienting the rotor into the wind was a complicated issue already for historical windmills. The first windmills able to rotate in order to "face" the wind appeared in the mid-18th century.Wind Power Plants, R. Gasch and J. Twele, Solarpraxis, Their rotatable nacelles were mounted on the main structure of the windmill using primitive wooden gliding bearings lubricated with animal fat. The necessary yawing torque was created by means of animal power, human power or even wind power (implementation of an auxiliary rotor known as fantail).

The yaw drives exist only on the active yaw systems and are the means of active rotation of the wind turbine nacelle. Each yaw drive consists of powerful electric motor (usually AC) with its electric drive and a large gearbox, which increases the torque. The maximum static torque of the biggest yaw drives is in the range of 200.000Nm with gearbox reduction ratios in the range of 2000:1.Bonfiglioli Power & Control Solutions Consequently, the yawing of the large modern turbines is relatively slow with a 360° turn lasting several minutes.

The elevator is a movable aerofoil that controls changes in pitch, the up-and-down motion of the aircraft's nose. Some aircraft employ an all-moving stabiliser and elevators in one unit, known as a stabilator or "full-flying stabiliser". The vertical tail structure (or fin) has a fixed front section called the vertical stabiliser, used to restrict side-to-side motion of the aircraft (yawing). The rear section of the vertical fin is the rudders, a movable aerofoil that is used to turn the aircraft's nose to one side or the other.

"Motorcycles, even racing designs, continue to feature what Cooper calls "styling aerodynamics" ... styling conventions and comfort demands make this sort of [rigorous] approach [to streamlining] impractical." Another factor making aerodynamic measurements relatively uncommon in the popular press is the lack of access to research- quality wind tunnels by journalists. Complete analysis of motorcycle aerodynamics would include measurement of drag, lift and side force at various speeds, wind angles, and rider postures; as well as pitching moment, rolling moment, and yawing moment (see yaw, pitch and roll for descriptions).

Ovoid-shaped fins with rudders were fitted at the wing-tips; also skids for support when static on the ground. The use of drag rudders was also investigated with the rudders opening in similar fashion to the airbrake, increasing drag on one side and yawing the aircraft. The centre of gravity was also adjustable in flight, with a 7 kg (15 lb) weight, on a fore-aft orientated threaded rod, which could be adjusted by the pilot. The sole prototype SP-821 first flew on 29 Mar 1949 piloted by Eng.

Ampaire is replacing the Cessna 337 Skymaster (a push-pull aircraft) forward piston engine with an electric motor. The forward Continental IO-360 piston engine is replaced with an electric motor powered by a battery in a parallel hybrid configuration, optimising power output to reduce operating costs and pollution. The centerline thrust makes the 337 a useful testbed, allowing thrust differences with no yawing unlike a conventional twin-engine aircraft. Ampaire is marketing the EEL to government departments and private owners while undisclosed commercial operators already placed orders.

This means that if the air temperature is higher and the aircraft has a higher altitude, the force of the operative engine will be lower, the rudder will have to provide less counteractive force, and so the VMCA will be lower. The bank angle also influences the minimum control speed. A small bank angle away from the inoperative engine is required for smallest possible sideslip and therefore lower VMCA. Finally, if the P-factor of the working engine increases, then its yawing moment increases, and the aircraft's VMCA increases as a result.

If an engine fails during taxiing or takeoff, the thrust yawing moment will force the aircraft to one side on the runway. If the airspeed is not high enough and hence, the rudder-generated side force is not powerful enough, the aircraft will deviate from the runway centerline and may even veer off the runway. The airspeed at which the aircraft, after engine failure, deviates 9.1 m from the runway centerline, despite using maximum rudder but without the use of nose wheel steering, is the minimum control speed on the ground (VMCG).

J. Bamber and C. H. Zimmerman (1933) Effect of stabilizer location upon pitching and yawing moments in spins as shown by tests with the spinning balance, NACA TN-474.M. J. Bamber and C. H. Zimmerman (1935) The aerodynamic forces and moments on a spinning model of the F4B-2 airplane as measured by the spinning balance, NACA TN-517.M. J. Bamber and C. H. Zimmerman (1936) Spinning characteristics of wings I : rectangular Clark Y monoplane wing, NACA TN-519. airfoils,C. H. Zimmerman (1933) Characteristics of Clark Y airfoils of small aspect ratios, NACA TN-431.

On his first couple of high altitude flights, Kit said his plane would snap into a spin when the motors burned out while approaching his peak altitude. He finally figured that the rocket motors were installed very slightly offset which, to keep it going straight, was causing him to have to cross control the plane increasingly as it accelerated. When the engines shut off, the cross-control condition, which was keeping the airplane from yawing, now became the perfect spin entry input. After two flights involving supersonic spin recovery, Kit was quick to neutralize the controls immediately upon motor shutdown in later flights.

The total lift acts at a distance x_{cp} ahead of the centre of gravity (it has a negative value in the figure), this, in missile parlance, is the centre of pressure . If the lift acts ahead of the centre of gravity, the yawing moment will be negative, and will tend to increase the angle of attack, increasing both the lift and the moment further. It follows that the centre of pressure must lie aft of the centre of gravity for static stability. x_{cp} is the static margin and must be negative for longitudinal static stability.

Profile drag caused by the deflected ailerons may add further to the difference, along with changes in the lift vectors as one rotates back while the other rotates forward. Waco VKS-7 cabin-class biplane with its pairs of quadruple ailerons linked by an external vertical connector to simplify its aileron control system. The ailerons on each side thus move either up or down together. In a coordinated turn, adverse yaw is effectively compensated by the use of the rudder, which results in a sideforce on the vertical tail that opposes the adverse yaw by creating a favorable yawing moment.

Dorsal view showing the pectoral fins The pectoral fins on most fish control pitching (up-and-down motion of the body), yawing (the side-to-side motion), and rolling. Most hammerhead sharks do not yaw or roll and achieve pitch using their cephalofoils. The smaller cephalofoil of a bonnethead shark is not as successful, so they have to rely on the combination of cephalofoils and their large pectoral fins for most of their motility. Compared to other hammerheads, bonnethead sharks have larger and more developed pectoral fins and are the only species of hammerhead to actively use pectoral fins for swimming.

Most rocket or missile configurations meet this criteria and the jet damping has a dynamic stabilizing effect. The jet damping torque rotates at nutation frequency in the spacecraft frame. The jet damping contributes to the pitch and yaw damping coefficients, Cm_q and Cn_r, where Cm_q is the rate of change of pitching moment with respect to pitch rate and Cn_r is the rate of change of the yawing moment with respect to yaw rate. For jet airplanes in cruise, the contribution of jet damping is usually negligible because the external aerodynamic damping is large relative to the jet damping.

Sukhoi Su-57 prototype suffering a compressor stall at MAKS 2011. Compressor axially-symmetric stalls, or compressor surges, are immediately identifiable, because they produce one or more extremely loud bangs from the engine. Reports of jets of flame emanating from the engine are common during this type of compressor stall. These stalls may be accompanied by an increased exhaust gas temperature, an increase in rotor speed due to the large reduction in work done by the stalled compressor and — in the case of multi-engine aircraft — yawing in the direction of the affected engine due to the loss of thrust.

Neither pilot aboard Flight 159 initially saw how close DAL 379 was to the runway. As Flight 159 sped down the runway, the captain observed that the DC-9 was "off the runway" by only "five, six, seven feet or something of that nature." As the Boeing 707 passed the Delta plane, the pilots heard a loud bang which coincided with a movement of the flight controls and a yawing motion of the aircraft. Thinking he had hit the DC-9, Flight 159's first officer attempted to abort the takeoff, and both pilots attempted to use their aircraft's thrust reversers, brakes, and spoilers to stop the aircraft.

A secondary control input that the rider can make is to lean the upper torso relative to the bike. As mentioned above, the effectiveness of rider lean varies inversely with the mass of the bike. On heavy bikes, such as motorcycles, rider lean mostly alters the ground clearance requirements in a turn, improves the view of the road, and improves the bike system dynamics in a very low-frequency passive manner. In motorcycle racing, leaning the torso, moving the body, and projecting a knee to the inside of the turn relative to the bike can also cause an aerodynamic yawing moment that facilitates entering and rounding the turn.

Yaw, Pitch and Roll in an aircraft Yaw motion in an aircraft A yaw rotation is a movement around the yaw axis of a rigid body that changes the direction it is pointing, to the left or right of its direction of motion. The yaw rate or yaw velocity of a car, aircraft, projectile or other rigid body is the angular velocity of this rotation, or rate of change of the heading angle when the aircraft is horizontal. It is commonly measured in degrees per second or radians per second. Another important concept is the yaw moment, or yawing moment, which is the component of a torque about the yaw axis.

At the time, it was believed that yawing and cavitation of projectiles were primarily responsible for tissue damage. Martin Fackler conducted a study with an AK-74 assault rifle using live pigs and ballistic gelatin; "The result of our preset test indicate that the AK-74 bullet acts in the manner expected of a full-metal-cased military ammunition - it does not deform or fragment when striking soft tissues". Most organs and tissue were too flexible to be severely damaged by the temporary cavity effect caused by yaw and cavitation of a projectile. With the 5.45 mm bullet, tumbling produced a temporary cavity twice, at depths of and .

The Sleep Book sets a good example for young kids on the proper hygiene methods used before bedtime such as brushing their teeth, putting their things away, and making sure their alarm is set for the morning. It has also popularly been used in Pre-K through Grade 1 to help kids with the pronunciation of their “sl” sounds. Throughout this story, Dr. Seuss introduces his young audience to a number of sleep related habits and activities: dreaming, sleep talking, sleep walking, yawing, and snoring. The book specifically indicates that it must be “read in bed” because of its ability to put kids to sleep.

One gunner remained at his post, directing bullets at the torpedo; but these were deflected by the water. The torpedo slammed into the ship's engine-room, tearing a gaping hole and knocking the steering gear out of action with an enormous explosion. The helpless ship was yawing out of control across the sixth and seventh columns of the convoy, narrowly missing collisions with other ships, before she lurched round in the opposite direction to that of the convoy and slowed to a standstill.Interviews with Commander J. Rankin (Dianella) and Commander P. L. Newstead, January 1963 The surviving ships rolled past her, and the convoy sped on in the fog.

This involves the simultaneous stimulation of two semicircular canals and is associated with a sudden tilting (forward or backwards) of the pilot's head while the aircraft is turning. This can occur when tilting the head down (to look at an approach chart or to write on the knee pad), up (to look at an overhead instrument or switch), or sideways. This can produce an overpowering sensation that the aircraft is rolling, pitching, and yawing all at the same time, which can be compared with the sensation of rolling down a hillside. This illusion can make the pilot quickly become disoriented and lose control of the aircraft.

Diagram 3 shows the running of wheelsets in a bogie or a four-wheeled vehicle. The wheelset is not running parallel to the track: it is constrained by the bogie frame and suspension, and it is yawing to the outside of the curve; that is, its natural rolling direction would lead along a less sharply curved path than the actual curve of the track.Yaw describes the situation when the longitudinal axis of the wheelset is not the same as the longitudinal axis of motion. The angle between the natural path and the actual path is called the angle of attack (or the yaw angle).

At lower turbine efficiencies the extra cost of the shroud must be justified, while at higher efficiencies the extra cost of the shroud has less impact on commercial returns. Similarly the added cost of the supporting structure for the shroud has to be balanced against the performance gained. Yawing (pivoting) the shroud and turbine at the correct angle, so it always faces upstream like a wind sock, can increase turbine performance but may need expensive active devices to turn the shroud into the flow. Passive designs can be incorporated, such as floating the shrouded turbine under a pontoon on a swing mooring, or flying the turbine like a kite under water.

When two opposing engines of aircraft with four or more engines are inoperative, there is no thrust asymmetry, hence there is no rudder requirement for maintaining steady straight flight; VMCAs play no role. There may be less power available to maintain flight overall, but the minimum safe control speeds remain the same as they would be for an aircraft being flown at 50% thrust on all four engines. Failure of a single inboard engine, from a set of four, has a much smaller effect on controllability. This is because an inboard engine is closer to the aircraft's centre of gravity, so the lack of yawing moment is decreased.

The Online Etymology Dictionary gives its origin as around 1683, when English colonists used it insultingly in reference to Dutch colonists (especially freebooters). Linguist Jan de Vries notes that there was mention of a pirate named Dutch Yanky in the 17th century. The Life and Adventures of Sir Launcelot Greaves (1760) contains the passage, "Haul forward thy chair again, take thy berth, and proceed with thy story in a direct course, without yawing like a Dutch yanky."The Life and Adventures of Sir Launcelot Greaves, Tobias Smollett, chapter 3 According to this theory, Dutch settlers of New Amsterdam started using the term against the English colonists of neighboring Connecticut.

The feathering system of the large, 8-bladed, 17.5-foot (5.33 m) diameter drag propellers must be automatic, very rapid and failure-free, to ensure the lowest possible propeller drag following a propulsion-system malfunction. If not, a failure of the feathering system of an outboard engine will increase propeller drag, which in turn enhances the thrust yawing moment considerably, thus increasing actual VMC(A). The control power generated by the small vertical tail and rudder alone is low by the small design. Only rapid reduction of thrust of the opposite engine, or increased airspeed can restore the required control power to maintain straight flight following the failure of a feathering system.

This was corrected, but was still the most technically advanced, intricate, and therefore time-consuming of the three to produce, which made it unattractive at that stage of the war. The G.55 was chosen for mass production, along with the C.205. The G.55 prototype reached 620 km/h (390 mph), fully loaded, and without using WEP (war emergency power), at 7,000 m (22,970 ft). This was a little less than expected, but it had a strong airframe and was the best aircraft regarding handling and stability at every altitude. The only negative assessment noted by G.55 pilots was the pronounced left-hand yawing at takeoff due to the powerful engine torque.

The state variables were chosen to be the angle of attack \beta and the yaw rate r, and have omitted the speed perturbation u, together with the associated derivatives e.g. Y_u. This may appear arbitrary. However, since the timescale of the speed variation is much greater than that of the variation in angle of attack, its effects are negligible as far as the directional stability of the vehicle is concerned. Similarly, the effect of roll on yawing motion was also ignored, because missiles generally have low aspect ratio configurations and the roll inertia is much less than the yaw inertia, consequently the roll loop is expected to be much faster than the yaw response, and is ignored.

The six degrees of freedom of movement of a ship Attitude degrees of freedom for an airplane The motion of a ship at sea has the six degrees of freedom of a rigid body, and is described as:Summary of ship movement Translation and rotation: # Moving up and down (elevating/heaving); # Moving left and right (strafing/swaying); # Moving forward and backward (walking/surging); # Swivels left and right (yawing); # Tilts forward and backward (pitching); # Pivots side to side (rolling). See also Euler angles The trajectory of an airplane in flight has three degrees of freedom and its attitude along the trajectory has three degrees of freedom, for a total of six degrees of freedom.

At the same time, to achieve the penetration required, Wallis designed the Tallboy to be very aerodynamically clean so that, when dropped from a great height, it would reach a much higher terminal velocity than traditional bomb designs. In the final design, the No. 78 Mark I tail of the bomb was about half the overall length of the finished weapon; the bomb casing was some of the overall length. Initially, the bomb had a tendency to tumble and the tail was modified; the fins were given a slight twist so that the bomb spun as it fell. The gyroscopic effect thus generated stopped the pitching and yawing, improving aerodynamics and accuracy.

At least one wing must be stalled for a spin to occur. The other wing rises, decreasing its angle of attack, and the aircraft yaws towards the more deeply stalled wing. The difference in lift between the two wings causes the aircraft to roll, and the difference in drag causes the aircraft to continue yawing. The spin characteristics diagramAerodynamics For Naval Aviators, Hurt, Revised January 1965, Issued by The Office Of The Chief Of Naval Operations Aviation Training Division, Figure 4.32 shown in this section is typical of an aircraft with moderate or high aspect ratio and little or no sweepback which leads to spin motion which is primarily rolling with moderate yaw.

The longitudinal centre of gravity affects the VMCA as well: the further from the tail it is, the lower the minimum control speed, because the rudder will be able to provide a larger yawing moment, and so it is easier to counteract the imbalance in thrust. The lateral centre of gravity also has an effect: the nearer the inoperative engine it is, the larger the moment of the working engine, and so the more force the rudder has to apply. This means that if the lateral centre of gravity shifts towards the inoperative engine, the aircraft's VMCA will increase. The thrust of most engines depends on altitude and temperature; increasing altitude and higher temperatures decrease thrust.

U-230s initial sortie began on 4 February 1943, when she left Kiel, arriving at Bergen on 9 February; she departed from Bergen on 11 February, for a war patrol east of Newfoundland with group Burggraf. The bad weather and difficult sea conditions encountered are described by Werner in his book: The weather was so bad that personnel on watch on the bridge were forced to wear rubber diving suits and eye masks. They had to be secured to the wildly pitching and yawing U-boat by steel belts. Below, it was no better, with bodies being hurled in all directions.Werner p90Blair p251 Burggraf had no success and was disbanded on 5 March, with U-230 and others forming the nucleus of group Westmark.

If the eight were bow rigged, the oar for the stroke (number 8) rower would be on the other side of the boat (bowside/starboard). There are other options, and in particular in fours the middle pair may row on the same side: this arrangement means that there is less yawing of the boat through the water throughout the course of the stroke, making it more efficient. The two rowers in the middle, rowing in a 'tandem', need to be well matched and synchronised to make this work (i.e. avoid clashing blades), and the bow person, rowing with a significant gap between them and stroke on their side of the boat, also needs to be able to adapt to the larger space in front of them.

Harrison had moved to London by 1737 and went on to develop H2, a more compact and rugged version. In 1741, after three years of building and two of on-land testing, H2 was ready, but by then Britain was at war with Spain in the War of Austrian Succession and the mechanism was deemed too important to risk falling into Spanish hands. In any event, Harrison suddenly abandoned all work on this second machine when he discovered a serious design flaw in the concept of the bar balances. He had not recognized that the period of oscillation of the bar balances could be affected by the yawing action of the ship (when the ship turned such as 'coming about' while tacking).

Wobble, shimmy, tank- slapper, speed wobble, and death wobble are all words and phrases used to describe a rapid (4-10 Hz) oscillation of primarily just the front end (front wheel, fork, and handlebars). Also involved is the yawing of the rear frame which may contribute to the wobble when too flexible.Roe, G. E. and Thorpe, T. E. "A Solution of the low-speed wheel flutter instability in motorcycles" Journal Mechanical Engineering Science V 18 No. 2 1976 This instability occurs mostly at high speed and is similar to that experienced by shopping cart wheels, airplane landing gear, and automobile front wheels. While wobble or shimmy can be easily remedied by adjusting speed, position, or grip on the handlebar, it can be fatal if left uncontrolled.

When a control surface is moved to present an angle to the oncoming airflow, it alters the airflow around the surface, changing its pressure distribution, and thus applying a pitching, rolling, or yawing moment to the aircraft. The angle of control surface deflection and resulting directional force on the aircraft are controlled both by the pilot and the aircraft's inbuilt control systems to maintain the desired attitude, such as pitch, roll and heading, and also to perform aerobatic maneuvers that rapidly change the aircraft's attitude. For traditional maneuvering control to be maintained, the aircraft must maintain sufficient forward velocity and a sufficiently low angle of attack to provide airflow over the wings (maintaining lift) and also over its control surfaces. As airflow decreases so does effectiveness of the control surfaces and thus the maneuverability.

Both stages of the suspension incorporate shock absorbers: the axlebox suspension has 2 friction shock absorbers per axle, and the central suspension has 5 hydraulic shock absorbers (on trucks with coil springs only). The car body rests on skid pads on the cast side flanges of the bolster; these skid pads are made of layered plastic, and serve to reduce the rolling and yawing movements of the trucks and car bodies. The car body is also connected to the center of the bolster by means of the central pivot—a vertical steel rod mounted in the center of the bolster, which transmits the traction and braking forces from the truck to the car body, and also receives part of the car body's weight. On the trailer cars, the trucks are similar to those of ordinary passenger cars, but have shorter frames.

Yak-52 using ailerons to roll counter-clockwise during an aerobatic maneuver Pairs of ailerons are typically interconnected so that when one is moved downward, the other is moved upward: the down-going aileron increases the lift on its wing while the up-going aileron reduces the lift on its wing, producing a rolling (also called 'banking') moment about the aircraft's longitudinal axis (which extends from the nose to the tail of an airplane). Ailerons are usually situated near the wing tip, but may sometimes also be situated nearer the wing root. Modern airliners may also have a second pair of ailerons on their wings, and the terms 'outboard aileron' and 'inboard aileron' are used to describe these positions respectively. An unwanted side effect of aileron operation is adverse yaw—a yawing moment in the opposite direction to the roll.

The 707's wings are swept back at 35°, and like all swept-wing aircraft, display an undesirable "Dutch roll" flying characteristic that manifests itself as an alternating combined yawing and rolling motion. Boeing already had considerable experience with this on the B-47 and B-52, and had developed the yaw damper system on the B-47 that would be applied to later swept-wing configurations like the 707. However, many pilots new to the 707 had no experience with this instability, as they were mostly accustomed to flying straight-wing propeller-driven aircraft such as the Douglas DC-7 and Lockheed Constellation. On one customer-acceptance flight, where the yaw damper was turned off to familiarize the new pilots with flying techniques, a trainee pilot's actions violently exacerbated the Dutch roll motion and caused three of the four engines to be torn from the wings.

Instrument panel of the V-Twin The Velocity V-Twin is a four-seat (with a five-seat option), retractable tricycle landing gear, composite construction aircraft with a twin engined pusher configuration and the canard layout of the Velocity XL single engine aircraft. Its fuselage is that of the XL-RG, with the addition of the single, vertical surface which replaces the twin end plate fins of the smaller XL. The aircraft features "gull wing" car-like doors and dual sidestick controllers. The flight control surfaces are the same as those of the XL. The aircraft's design goal was to offer the safety of twin engines without the stall and spin risks of a conventional twin during single-engine operations. The rear-facing pusher propellers are mounted close together where the fuselage cross-section tapers, reducing asymmetrical single-engine thrust yawing compared to conventional twin-engine aircraft.

WW1 Aero – The Journal of the Early Aeroplane No.196, May 2007: Preston Watson's Aeroplanes To execute a banked turn from flying straight and level, the rocking wing worked moderately effectively, but when the aeroplane's lateral equilibrium had been compromised, tipping the rocking wing in the opposite direction to the down-going wing to right itself had a tendency to yaw the aircraft in that direction. In effect, the rocking wing did not fully assist in correcting conditions of instability since the pilot had no means with which to induce or correct a yawing motion. Another possible reason behind the rocking wing idea not progressing beyond Watson's experiments was that it could only be applied to relatively light and small aircraft. Had Preston Watson survived, it is possible that with continual experience flying his aeroplanes he would have thought up an ingenious solution to this problem.

Wadcutter or Flathead pellets A .177 (4.5mm) caliber "Wadcutter" pellet next to a stick of chewing gum The most popular ammunition used in rifled air guns is the wasp-waisted diabolo pellet, which has two sections – a solid front portion called the "head", which contains the center of mass and is available in a variety of shapes and styles such as flat (wadcutter), round (domed), cone-shaped (pointed) and pitted (hollow point); and a hollowed, thin-walled conical rear portion called the "skirt", which expands and fully engages the bore to provide a good seal and thus allows maximal efficiency in pellet propulsion during shooting. In flight, the skirt has greater drag-to- weight ratio than the head and exerts a rearward pull behind the center of mass, similar to that of a shuttlecock. This produces a phenomenon known as drag stabilization, which helps to counteract yawing and maintain a consistent flight path.

Waddy, A Tour of the Arnhem Battlefields, p. 42 The brigade was scheduled to arrive on the second day of the operation, 18 September, using drop zones protected by elements of 1st Airlanding Brigade.Thompson, p. 210 In the event, ground mist in England meant that the second lift was delayed by four hours,Middlebrook, p. 225 which spared the Dakota transport aircraft from meeting Luftwaffe fighters over the drop zone.Waddy, A Tour of the Arnhem Battlefields, p. 98 Nevertheless, the aircraft encountered considerable anti-aircraft fire as they approached the drop zone. Waddy later recalled that his aircraft was so near to the ground that he could see the upturned faces of the German gun crews. He observed numerous flak bursts and watched the escorting Hawker Typhoon fighters attacking flak batteries as they approached the DZ.Waddy, A Tour of the Arnhem Battlefields, p99 His own aircraft was hit in the tail but the pilot continued to the drop zone where, despite bad yawing, Waddy and his men were able to jump.