57 Ground Effect Vehicles

 Introduction

Ground Effect Vehicles (GEVs) utilize an interactional aerodynamic phenomenon known as “ground effect.” This phenomenon, perhaps only loosely understood by some engineers, occurs when airflows interact with an external impervious surface, such as the ground. The consequence of this interaction for a GEV is a significant increase in static pressure below its surfaces, thereby creating an upward lifting force to support some or all of its weight. One question that immediately arises is whether such machines are ground vehicles, sea vessels, or air vehicles. The answer is that they are potentially all of them!

A hovercraft, also known as an air-cushion vehicle (ACV), is one type of GEV that creates lift and “flies” using ground effect. The hovercraft rides on a combination of a so-called “cushion” of higher-pressure air below the vehicle inside the inner plenum as well as a jet thrust contribution from a radial “momentum curtain” of downward flow that flows between the inner and out plenums, as shown in the schematic below. This higher-pressure air and momentum jet originates from an engine driving a fan, for which the excess pressure generated may also be used to direct bleed air through horizontal jets for forward propulsion and control.

A cross-section of a simple hovercraft using a fan to create a lifting stagnation pressure in a plenum augmented by the lift produced by a momentum curtain.

The name “hovercraft” is a trademarked name of Saunders-Roe, an aircraft and maritime engineering company. However, a hovercraft has since become synonymous with all air-cushioned vehicles that can hover free of the ground. An example of a modern hovercraft is shown in the photograph below, which, in this case, is being propelled over water by two ducted fans with steerable rudder vanes or ruddervators. The name “hovercraft” is also known as “Aeroglisseur” (in France), “Luftkissenboot” (in Germany), and “Ground Effect Machine” (in the U.S.).

A commercial hovercraft, which in this case operated over water as a shuttle service to and from an offshore airport in Japan.

Hovercraft are operated by a pilot, much like an aircraft rather than a marine vessel. However, the classification of the vehicle as an aircraft per se is debatable. Nevertheless, a hovercraft can fly free of the ground using aerodynamic lift, so it is technically, on the one hand, an aircraft. On the other hand, it can operate as a marine vehicle, so specific additional naval architectural design and seaborne requirements apply, including a need for floatation. Hence, a hybrid vehicle classification for a hovercraft is also appropriate. Hovercraft can travel easily over rough surfaces, including long grass, brush, water, land, mud, and snow, making them rather unusual but highly versatile vehicles for many civil applications and military missions.

Another type of GEV uses the wing-in-ground-effect (WIGE) concept, which rides on a region of higher-pressure air below the vehicle and the ground that creates lift for reasons similar to that of a hovercraft. However, a wing-in-ground-effect (WIGE) vehicle cannot hover and needs forward airspeed to produce lift on its wings; this lift force is significantly increased by the proximity of the wing to the surface, as shown in the schematic below. Besides the increased stagnation pressure below the wings, sometimes called a “ram-air” effect, ground effect pushes the wing tip vortices laterally further away from the wings, significantly increasing their effective aspect ratio and reducing their drag. The upshot of these beneficial aerodynamic effects is that a WIGE vehicle can skim efficiently over the water at airplane speeds, e.g., more than 100 knots, but only if it maintains relatively low altitudes of less than a wingspan.

A WIGE vehicle takes advantage of an increase in aerodynamic lift and a reduction in drag.

The concept of WIGE vehicles is not new, and they continue to be explored for military applications, cargo transportation, and even recreational use. Other names for such vehicles include “surface effect ship” and “surface skimmer.” These rather unusual-looking vehicles perform running takeoffs and landings from the water like a seaplane, but they do not have any contact with the water while in “flight.” Some WIGE concepts may also be able to travel over relatively flat ground like a hovercraft, but they are designed for water operations like a seaplane; they cannot take off from any other surface.

A WIGE design that uses the “reverse-delta wing” concept, which can also fly out of ground effect, is shown in the photograph below. This vehicle skims over water at speeds that are four or five times those of most watercraft. It is unsurprising, therefore, that WIGE vehicles must be operated at least partially according to maritime regulations. Consequently, the International Maritime Organization (IMO) has issued guidelines for wing-in-ground vehicles (they refer to it as a “WIG craft”) in the context of other marine vehicles, including safety and navigational requirements. Nevertheless, a WIGE vehicle is still technically an aircraft and is generally piloted as one, just like a hovercraft, which is considered more of an aircraft than a marine vehicle.

The Airfish is a modern wing-in-ground effect vehicle, which, in this case, can also fly out of ground effect like an airplane.

Look! That’s a funny-looking boat! Nope, it’s a funny-looking airplane!

The U.K. aviation authorities remain at odds with the European Union (EU) and the U.S. over the classification and regulation of wing-in-ground effect (WIGE) vehicles. The U.K. Civil Aviation Authority (CAA) insists WIGE vehicles should be classified as aircraft. In contrast, the European Aviation Safety Agency (EASA) and the U.S. Federal Aviation Authority (FAA) classify WIGE vehicles as marine vehicles. One day, the authorities will sort it all out and reach a consensus. In the meantime, we should be neutral and refer to the concept simply as a “vehicle.” Nevertheless, it might be worthwhile for potential pilots and operators of WIGE vehicles to obtain maritime certifications and a pilot’s license with a seaplane rating.

Learning Objectives

  • Review the developmental technical history of ground-effect vehicles (GEVs) such as hovercraft and wing-in ground-effect (WIGE) vehicles.
  • Learn about the anatomy and unique design features of such ground-effect vehicles and how they work.
  • Study the basic aerodynamic theory behind lift production on hovercraft and other ground-effect vehicles.
  • Appreciate the valuable performance characteristics of GEVs and their limitations.

History

Like most flight vehicles, the ideas of developing “ground effect” and “air-cushioned” vehicles go back over a century. John Thornycroft patented an early concept for an air-cushioned boat in 1877, proposing that the air cushion would reduce the surface contact area of the boat’s hull with the water, thereby reducing its drag and increasing its speed over the water. He built a catamaran model and used a bellows mechanism driven by a wound-up spring to trap pressurized air between the two hulls. The resulting overpressure lifted the boat partially out of the water, allowing it to glide just above the surface, markedly increasing its speed. Thornycroft needed a powerful engine to make it practical on a bigger scale. Still, it was not until the 1920s, with advancements in internal combustion engines, that proper hovercraft and other GEVs became more viable. In many ways, the availability of engines with high power-to-weight ratios for use in GEVs paralleled the tipping point in the successful development of helicopters.

Hovercraft

In 1915, Dagobert Müller von Thomamühl modified a speedboat by pumping air below its hull. His idea was similar to that of Thornycroft: to reduce hull drag as the boat traveled over the water. Thomamühl’s modified speedboat reportedly achieved a speed of over 32 knots, more than twice the speed of the original boat. However, despite being able to lift itself partially out of the water, it could not hover. The availability of suitable engines powerful enough to drive a rotor or fan soon led to designs that created higher-pressure air to form a “cushion” below the vehicle. In 1932, Toivo Kaario was perhaps the first to develop an air cushion vehicle (ACV) or hovercraft-type ground-effect vehicle using this ground cushion effect. His prototype, dubbed pintaliitäjä (surface hoverer or hovercraft), shown in the photograph below, used a fan driven by a Harley-Davidson motorcycle engine. It was tested until about 1935 with some modest success, and although Kaario obtained Finnish patents for the design, it was not developed further because of a lack of funding.

In the 1930s, Toivo Kaario developed a small personal hovercraft using a fan driven by a motorcycle engine.

In the mid-1930s, Vladimir Levkov developed a series of ACVs that could hover above ground or water. The L-1 prototype had a simple design consisting of a wooden catamaran with two hulls separated by a cavity under pressure, following Thornycroft’s ideas and previous work. Further development continued with a series of other prototype machines of increasing refinements and performance. One of Levkov’s ACVs, called the fast-attack L-5 boat or “hover tank,” as shown in the photograph below, achieved a speed of 70 knots (130 kph); there is also a surviving film of its flights. Levkov led the development of several other ACVs, including the much more capable L-11, but these vehicles were destroyed during WW2. During WW2, Charles Fletcher in the U.S. designed a hovercraft called a “Glidemobile.” This design also worked on trapping pressurized air in a plenum to lift it from the surface. However, the U.S. government classified the concept shortly after testing, and the prototype was never developed further.

Levkov’s L-5 fast-attack boat, or “hover tank,” was one of the first hovercraft concepts.

Significant developments in hovercraft technology occurred after WW2. Christopher Cockerell is widely recognized as the foremost pioneer in the development of modern hovercraft. In 1950, he disclosed his ideas of a hovercraft in British Patent GB854211A in which a radial air jet created a reaction “momentum curtain” force and an excess pressure beneath the vehicle, allowing it to hover and travel above ground or water. Cockerell’s design, which added a flexible rubber skirt to trap the air cushion, significantly improved on certain limitations of earlier hovercraft designs. He built a small demonstrator of his hovercraft concept to market it. However, shipbuilding companies claimed his invention was an airplane, and aircraft companies claimed it was a ship, so neither were interested. Nevertheless, a demonstration of the concept in front of British Government officials led to a grant for further development, but they also declared it top-secret technology.

Christopher Cockerel patented the hovercraft design with a peripheral “momentum curtain” to augment lift production.

The first technically successful hovercraft was the SR-N1 (Saunders-Roe Nautical Model 1), which was a demonstrator built under the design leadership of Cockerell, and its first flights were made in June 1959. The initial version had a circular structure that looked somewhat like a “flying saucer,” a name coined by the press; later versions had a bow that was more like a boat to aid its movement over water, as shown in the photograph below. It was primarily made of riveted aluminum stressed skin like an aircraft, with a separate buoyancy tank for floatation. It used a 450-hp (336 kW) radial aircraft engine that drove a large fan in a duct below an intake nozzle to generate the air cushion beneath the machine, allowing it to hover in ground effect. Directing some bleed air through ducts to nozzles, rudders, or vanes gave translational speed and directional control. The pilots sat in a small cockpit just forward of the duct. The SR-N1 made many successful demonstrations of hovercraft technology, including a flight across the English Channel, and it paved the way for the rapid development of bigger and more capable concepts.

The first technically successful hovercraft was the SR-N1, built under Cockerell’s design leadership and first flew in June 1959.

Melville Beardsley developed several hovercraft designs in the 1950s and 1960s and founded the National Research Associates (NRA). NRA developed and tested several ACVs, with the Aqua-GEM being sold in limited numbers. The company also sold several small personal hovercraft, including the “Little Skimmer.” The company was wound up in the late 1960s after being embroiled in patent disputes with the British hovercraft industry. William Bertelsen built a hovercraft concept in 1959 called the Aeromobile 35-B, which was followed by another series of prototype designs, including the Aeromobile-200, as shown in the photograph below. There is also a film of one of his hovercraft traveling down the streets of Chicago. None of his concepts, however, were to go into production.

William Bertelsen built a prototype hovercraft in 1959 called Aeromobile, which he also flew down the streets of Chicago. It was not developed further.

By the early 1970s, the basic hovercraft concept had been considerably developed technically, and larger and more capable hovercraft began to find several useful if not niche, roles in both civil and military applications. The Sauders-Roe company continued to develop a series of hovercraft models with increasing capabilities, including the enormous SR-N4, as shown in the photograph below. The SR-N4 and its variants were used to carry up to 400 passengers and 30 vehicles across the English Channel from Ramsgate and Dover in England to Calais and Boulogne in France, respectively. The SR-N4 weighed over 250 tons and was powered by four turboshaft engines driving variable pitch propellers that could also swivel \pm30 degrees on azipods. It had a cruise speed over the water of 65 knots, making the cross-channel trip in only 30 minutes, about four times as fast as a regular sea ferry. However, such large hovercraft were operationally expensive and not very profitable. With the opening of the Channel Tunnel in 1994, the last two operational SR-N4 hovercraft became obsolete and were retired in October 2000 after an impressive 30 years of continuous service.

For over 30 years, the massive SR-N4 hovercraft carried millions of passengers and vehicles across the English Channel.

Today, various branches of the armed services, especially the Marines, use hovercraft or air cushion vehicles (ACVs) for amphibious operations and search-and-rescue. These ACVs mainly transport personnel, weapons, vehicles, equipment, and cargo over diverse terrain. The photograph below shows the Landing Craft Air Cushion Vehicle (LCACV), a high-speed hovercraft and fully amphibious landing craft. It can carry a payload of up to 70 tons, such as trucks, support vehicles, and even an M-1 tank, and land on almost any shoreline worldwide. These fantastic vehicles have proved their worth to armed forces worldwide for several decades.

A Marine Corps hovercraft or LCACV used for amphibious operations can carry trucks or a tank.

The flexibility and speed of hovercraft over water and other terrain also make them suitable for several important service roles, such as patrols and rescue work, and there are many manufacturers worldwide who supply hovercraft for these purposes. Smaller hovercraft are used in Britain as a part of the inshore fleet operated by the Royal National Lifeboat Institute. They have been used, with great success, on large areas of tidal mudflats or sand where the surface is too soft to support land vehicles and the water is too shallow for boats.

Smaller types of hovercraft are used as sporting vehicles or for fishing and hunting in diverse terrain. Like their larger counterparts, these hovercraft can easily traverse a wide range of terrain, cross rivers, lakes, snow, thin ice, etc. They can reach places often inaccessible by any other vehicle so that they may be the epitome of amphibious transportation. Some types of single-person sporting hovercraft are used for racing, as shown in the photograph below.

A small personal hovercraft that can be used for numerous recreational and sporting purposes.

Wing-in-Ground-Effect Vehicles

The first practical use of the wing-in-ground effect (WIGE) phenomenon was in 1929 by the enormous Dornier Do X flying boat, which was found to achieve a considerable gain in its flight range by skimming close to the ocean’s surface. In wind tunnel tests, it was also found that the vertical proximity of a lifting wing to a ground surface affected both its lift and drag, with beneficial effects when less than a chord length above the surface. One reason is the reduced induced drag because of the laterally outward movement of the wing tip vortices near the ground. Pilots also became aware of ground effect in the landing flare, which helped cushion the landings, but if the airspeeds were too high, they would also “float” down the length of the runway.

Rostislav Alexeye of the Russian Central Hydrofoil Design Bureau developed the first of a series of specifically designed Wing-in-Ground-Effect (WIGE) vehicles, also known as ekranoplans (meaning “screenplanes”). The SM-1, powered by a single jet engine with two lifting wings, took its first flight in July 1961. The improved SM-2, which flew in March 1962, had a single main wing and large vertical and horizontal stabilizers, shown in the photograph below. This vehicle incorporated a secondary turbojet engine in its nose to blow air toward the main wing, thereby creating more lift at lower speeds, known as power-augmented lift. During the Cold War, several other WIGE vehicles were explored for various military applications, including troop transport and anti-submarine warfare, but none made it to operational service. Nevertheless, development activities on such ground-effect vehicles continued through the 1960s.

The SM-2, which flew in March 1962, had a single main wing and large vertical and horizontal stabilizers with a secondary turbojet engine to blow air at the wing to increase its lift.

The first flight of the massive KM (Korabl Maket) ekranoplan, as shown in the photograph below, occurred in August 1967. The vehicle had a cruise speed of 267 mph (430 km/h) and a maximum speed of 311 mph (500 km/h). The KM had a gross weight of 544,000 kg (1,199,313 lb), with a range of 1,500 km (932 miles). The aircraft first appeared to observers on satellite images during its trials at the Caspian Sea, its unusual shape raising many questions about what it was and gaining the moniker “Kaspian Monster” or “Caspian Sea Monster.” It underwent trials and other developments and improvements through the 1980s.

The KM (Korabl Maket) ekranoplan saw trials at the Caspian Sea in the late 1960s and became known as the “Caspian Sea Monster.”

The KM design became the basis for the Lun-class ekranoplan developed in the 1980s, which saw one example enter service with the Soviet Navy and later the Russian Navy. This massive missile-carrying S-31 (MD-160) Lun (“Harrier“), as shown in the photograph below, was powered by eight turbojet engines mounted on a foreplane. While only one vehicle was built, it had a maximum takeoff weight of 380,000 kg (837,756 lb) with a payload of up to 137,000 kg (302,000 lb) and a range of 2,000 km (1,243 miles) at a speed of over 200 knots. It could launch up to six cruise missiles and was a potentially formidable weapon, able to evade both sonar and radar; fortunately, it was never used in earnest and was retired from service in the late 1980s.

This Lun-class ekranoplan, the MD-160, was a massive missile-carrying vehicle powered by eight turbojet engines.

Alexander Lippisch designed a WIGE vehicle in the late 1960s. Lippisch was an ambitious and forward-thinking aeronautical engineer who had initially worked for the Zeppelin company in Germany. Lippisch became interested in tailless and other unorthodox aircraft, and significantly advanced aircraft designs of the WW2 era soon followed. His most famous design was the Messerschmitt Me 163 rocket-powered interceptor, which saw limited use during WW2 but led the way for future swept-wing aircraft designs. Lippisch patented a WIGE design with a “reverse-delta” wing shape with an unswept leading edge but a highly swept trailing edge, as shown in the figure below. Of note also is the significant anhedral on the wing, which helped capture the air cushion effect.

In the late 1960s, the forward-thinking aeronautical engineer Alexander Lippisch patented a “reverse-delta” wing for a ground-effect vehicle.

Lippisch’s patent was sold to Rhein-Flugzeugbau (RFB), resulting in the X-113, as shown in the photograph below. Anhedral on the wing was found to maintain the benefits of ground effect to a higher cruise altitude over the water, allowing it to operate over rougher seas. It even demonstrated its ability to fly well out of ground effect to about 1,000 ft (330 m). The wing tips had winglets to increase the effective aspect ratio of the wings and reduce drag, and wing-tip floats to give stability on the water. A T-tail fin and tail fin were located at the end of a long dorsal fin, the large tail surfaces giving sufficient stability and control. One of the adverse characteristics of WIGE aircraft is a relatively significant shift in its center of pressure as it moves in an out-of-ground effect, leading to a pitch instability, so a sizeable horizontal tail and good elevator authority are required. The first flight of the X-113 was made in October 1970, and tests continued until 1974, but the vehicle did not go into production. However, many WIGE vehicles are derivatives of the reverse delta wing concept, such as the Airfish, Eska, and XTW, which have shown that high lift-to-drag ratios of 20:1 are achievable with this type of reverse delta wing. 

Lippisch’s WIGE concept became the X-113, powered by a 40 hp (30 kW) engine driving a propeller.

There has been intermittent interest in WIGE vehicles over the last few decades. DARPA evaluated the Aerocon “Wingship” design as part of a technical study of the WIGE concept for military uses during the 1990s. However, the idea did not progress. In 2002, Boeing’s Phantom Works unveiled a WIGE called the Pelican. It would have been the biggest and heaviest aircraft ever built, but the project seems to have faded into obscurity. However, the WIGE concept has recently received renewed attention from various aerospace companies and government organizations, such as DARPA, who have proposed the renewed consideration of such a surface skimmer ground effect vehicle for efficient, long-range, heavy-lift transport over oceans. The DARPA Liberty Lifter program aims to develop a vehicle similar in size and payload capacity to the C-17 transport aircraft; an artist’s impression of one concept is shown in the figure below. It remains to be seen whether such a vehicle will be realized, although the benefits of it enhancing the long-reach and “under the radar” military capabilities remain attractive.

A conceptual design of a large ocean-crossing WIGE aircraft designed under DARPA’s Liberty Lifter program.

Anatomy of GEVs

The anatomy of GEV vehicles, which encompass various hovercraft and wing-in-ground effect concepts, is somewhat mysterious to most people, even engineers. Their principle of operation is relatively straightforward/ However, the aerodynamics underlying their performance and handling characteristics require a deeper understanding. Both vehicles work under the much-coined “ground cushion” effect, which results from redistributed air pressure below and above the vehicle, leading to an enhanced lift force to overcome its weight. It should be appreciated that even slight pressure differences can generate significant lift forces when they act over large surface areas.

Hovercraft Anatomy

The anatomy of a generic hovercraft is shown in the schematic below. The ground cushion between the vehicle and the surface is created using one or more engine-generated fan combinations. Piston or turboshaft engines can be utilized, although turbocharged marine diesel engines are also popular for modern hovercraft. The fan, sometimes called an impeller, draws in air to increase its static pressure. Either axial or centrifugal fans can be used. The fan must have high efficiency, so it requires carefully designed blades with appropriate airfoil sections, blade twist, and planform shape. This higher-pressure air is channeled and distributed in a plenum beneath the vehicle, creating a lift force that helps the vehicle to rise just above the surface, as illustrated in the figure below.

The general anatomy of a hovercraft.

Lift Fan(s)

While the fan may produce some vertical lift, depending on its design, i.e., axial or centrifugal, this is only a fraction of the lift produced by the increased static pressure below the vehicle. The flexible skirt or curtain produces the remainder of the lift forces, directing airflow as a slightly inward-angled jet that impinges on the surface. The effect gives an additional momentum lift on the vehicle over and above the pressure force created in the plenum, called the “momentum curtain,” after the concepts advanced by Cockerell.

Increasing the power delivered to the fan increases its rotational speed, so the static pressure and the height above the surface increase. However, when this happens, more air escapes below the skirts, and the pressure cushion effect diminishes. The vehicle reaches an equilibrium height when the bottom of the skirt is a short distance above the surface; the judicious application of engine power can regulate the ride height.

Engines

One or more engines can power hovercraft. Smaller hovercraft may use one engine with the drive split through a gearbox, delivering power to the lift fan and the remaining power to the propulsion system. Other hovercraft may use ducting to allow one engine to perform both tasks by directing some air to the skirt and the remaining air out of horizontal ducts for propulsion. On hovercraft with several engines, one usually drives the lift fan, and the other engines drive propellers or fans. Larger, heavier hovercraft may incorporate variable-pitch and reversing-pitch propellers that can swivel on azipods for better performance and control.

Propulsion is a vital aspect of hovercraft design, and modulation of the thrust is essential for forward, backward, and lateral movements. To this end, hovercraft may use differential propeller pitch, rudders, and/or vectored thrust to achieve control. Rudders assist in yaw (directional changes), while vanes below the fan or inside the plenum can be utilized to control the mass flow rate from the fan to regulate pressure and, hence, give pitch and roll control. Modern hovercraft may also have control systems that augment stability and responsiveness to control inputs.

Skirt

An essential part of the anatomy of a hovercraft is its flexible rubber skirt, which extends around the periphery of the hovercraft and encapsulates the pressure plenum. A secondary skirt or curtain with inward-pointing independent, flexible extensions known as fingers allows the skirt to deform when striking an obstacle or traversing uneven land or choppy seas, minimizing pressure loss below the vehicle. While other concepts may be used, skirts must be flexible and adaptive to accommodate changes in surface contours and maintain an effective seal.

Stability

The skirt also gives an inherent pitch and roll stability to a hovercraft. For example, if a disturbance causes the vehicle to pitch or roll, as shown in the figure below, then the distance from the bottom of the curtain to the ground increases on one side, allowing more air to escape and reducing pressure and less air to escape on the other, increasing pressure. The net effect, therefore, is a restoring moment on the vehicle that will cause it to self-right itself. However, there may be a considerable lag in the build-up of the restoring moment because of the vehicle’s inertia.

A hovercraft has good positive static stability in pitch and roll, which naturally keeps it on an even keel.

Roll and pitch stability and a finer level of control can also be achieved by inflated compartments dividing the skirt and, hence, the ground cushion into compartments. The air pressure can then be modulated to obtain pitch and roll control. Proper weight distribution is also crucial for stability and control. An evenly distributed load helps prevent tilting or leaning to one side, and pilots need to ensure that the vehicle is loaded within its defined weight and balance envelope. Sometimes, hovercraft can be equipped with water ballast systems to adjust their weight distribution. Hovercraft designed for maritime use also need to exhibit good sea-keeping abilities, especially in their ability to negotiate waves.

Control

A hovercraft has unlimited directional movement over a surface and is more difficult to control than a boat or a terrestrial vehicle. Therefore, this issue gives rise to unique problems in its control, i.e., getting the machine’s center of gravity where it needs to go and in the correct direction. Methods used include aerodynamic control surfaces (e.g., rudders), differential thrust, thrust vectoring, differential plenum pressure, and air jets. Control surfaces, such as rudders in the slipstream of a propeller, provide an effective and responsive means for directional control. However, their effectiveness is reduced at lower airspeeds and low thrusts. Adverse coupling between yaw and roll can occur if the center of pressure of these surfaces is high relative to the center of gravity of the vehicle. Another method of control is to use pressurized bleed air that is ejected through nozzles mounted at appropriate locations to give yawing moments and side forces. However, their response time is relatively long, so pilots must anticipate the vehicle’s behavior well in advance.

 

Methods of steering a hovercraft include aerodynamic rudders, differential propulsor thrust, thrust vectoring, or combinations of these methods.

Differential thrust can be produced on twin propellers mounted laterally side by side by controlling the propeller pitch angles and/or rotational speeds. In this fixed side-by-side propeller configuration, the thrust is parallel to the vehicle’s longitudinal axis, so this approach introduces a turning/speed coupling effect. The vehicle must also operate with some yaw angle to provide a lateral force to balance the centrifugal forces during a turning maneuver, as illustrated in the figure below. Higher centrifugal forces on larger vehicles during turns mean that thrust vectoring is the best method to achieve directional control, which can also be balanced using rudders. Water rudders can also be deployed for over-water operations to help give better control and tighten the turn radius.

A hovercraft must perform a “flat” turn, which requires careful use of differential thrust (if available) and rudder controls.

The yawing moment and side force required for directional (yaw) control can also be generated using fore and aft swiveling pylon-mounted propellers on azipods. For some designs, the swivel angle must be limited on either side of the longitudinal axis to limit the magnitude of the adverse rolling moment on the hovercraft relative to its center of gravity. Compared with the fixed side-by-side propeller arrangement, swiveling pylon-mounted propellers can generate a higher yawing moment because the propellers can be mounted further from the vehicle’s center of gravity, and less forward thrust is lost for a given yawing moment. Aerodynamic rudders can help balance the turn to minimize the yaw angle, which may need cross-controlled inputs.

WIGE Anatomy

By design, this type of flight vehicle uses the benefits of ground effect to lift itself above the water’s surface, but it still flies close to the surface, usually less than half a wing span. Such WIGE vehicles can achieve high cruise speeds over surfaces like water with good aerodynamic efficiency. Much of the power needed from the engines is for takeoff to overcome the hydrodynamic drag from the water. Once airborne and settled at an equilibrium height in the ground effect condition, the drag reduces significantly, and the vehicle can then cruise relatively fast at significantly reduced power. Cruise speeds of 200+ knots are entirely possible. There are three types of WIGE vehicles, as shown in the figure below: an ekranoplan, a reverse delta wing, and a tandem wing. They are distinctive from conventional subsonic airplanes because of their characteristically small aspect ratio of the main wing, the addition of endplates and floats, and unique fuselage/hull shapes to allow them to take off and land on water.

 

There are three types of WIGE vehicles: An ekranoplan, a reverse delta wing, and a tandem wing.

The more detailed anatomy of a wing-in-ground effect vehicle (WIGE), also known as an ekranoplane (after the Russian concept), is shown in the schematic below. Ekranoplans are typically powered by turbojet or turboprop engines, providing the necessary thrust for lift and propulsion. The number and placement of engines depend on the specific design and size of the ekranoplan. Placing the engines on a foreplane canard allows the jet exhaust to be directed downward toward the wings, increasing their lift. The lift augmentation by the propulsive system can be significant, helping the vehicle transition from the high drag of being seaborne into free flight like an airplane. Full-span trailing edge flaps on the wing help trap the higher-pressure air below the wings to give the “ram air” effect, helping shorten the takeoff distance over the water.

 

The general anatomy of a wing-in-ground effect ekranoplan.

Wings

Like all WIGE vehicles, ekranoplans have large surface area wings but are relatively short in wing span and have a fairly low aspect ratio, perhaps between 2 and 3. It is well known that higher aspect ratio wings give the least induced drag but at the price of higher structural weight. But for a WIGE vehicle, the ground effect condition increases the stagnation pressure below the wing and pushes the wing tip vortices further away from the wing. This effect increases the wing’s effective aspect ratio and gives the benefits of lower induced drag for a lower aspect ratio wing, hence saving structural weight. Flotation sponsons are needed at the tips of the wings, which give the vehicle lateral stability on the water.

Fuselage/Hull

Like an airplane, the fuselage of a WIGE vehicle houses the cockpit and other essential flight systems, including volume for a payload. However, unlike an airplane, the fuselage must be designed to be aerodynamic and hydrodynamic. Indeed, the hydrodynamic loads on the hull are significant during water-borne operations, and the structure must be designed for increased strength and stiffness compared to an airplane to carry the hydrodynamic loads at the expense of structural weight. The design requirements are similar to those of a seaplane.

Empennage

Like all aircraft, WIGE aircraft have an empennage comprising horizontal and vertical stabilizers. The horizontal tail must have a significant area and control authority to compensate for the change in pitching moment if the vehicle reaches an altitude that comes out of ground effect. A large dihedral angle on the horizontal tail can help significantly with lateral stability, the main wing having either minimal dihedral or even anhedral, thereby making no contribution to stability. Anhedral can help maintain the benefits of ground effect to a greater altitude over the water, which can benefit operations in rough seas.

Control

The control of WIGE vehicles is similar to that of hovercraft. Turns are made in a horizontal plane, for which the balance of centrifugal and aerodynamic forces must be considered. as shown in the figure below. Wide-radius skidding turns are the norm, depending on the thrust available and rudder authority. Suppose the vehicle can fly a little higher off the ground or water. In that case, banking using the differential application of the flaperons can increase the bank angle to control the turn. However, the proximity to the ground may severely limit the bank angle.

Large-radius skidding turns are the norm for WIGE vehicles.

Hovercraft Performance

Two types of hovercraft require analysis. The first is the pure plenum type, in which the vehicle is lifted entirely by the fan’s increased pressure differential. The second is the plenum type, augmented by a “momentum curtain” or peripheral jet, where a combination of differential plenum pressure and the reaction force of a peripheral jet impinging on the ground share in the lift production. It is known that the latter type is preferred for a hovercraft, which creates more lift, but both types are worthy of analysis to bring out the performance and design characteristics.

Both can be analyzed, at least in the first instance, by applying the conservation principles of mass, momentum, and energy in their integral form. The published literature shows that the theory of hovercraft comes up in two different fluid dynamic contexts. The first theory is a plenum discharge analysis originating in internal flow theory. The second comes from the aerodynamic theory for a lift fan. As will be shown, both theoretical approaches lead to the same results for the power required to lift a hovercraft off a surface to a certain hover height.

Plenum Discharge Theory

The radial fluid discharge from a plenum chamber forms one mathematical foundation for analyzing the hovercraft. The figure below shows the cross-section of the control volume of a simple hovercraft that uses the pure “plenum” type to lift the vehicle. A fan draws air from the ambient atmosphere at pressure, p_a, and does work on the air to raise the static pressure by \Delta p, then to a stagnation pressure, p_0, inside a plenum of large volume where the flow velocity approaches zero. The resulting differential “cushion” pressure, i.e., p_0 - p_a acting over the surface area of the plenum, then becomes the primary source of the lift force on the vehicle, L, to overcome its weight, W, i.e.,

(1)   \begin{equation*} L = W = \left(p_0 - p_a \right) \left( A_c - A_f \right) \end{equation*}

where A_c is the effective lifting area of the cushion below the vehicle, and A_f is the fan area. It can be assumed that the air induced by the fan continuously and steadily escapes from under the vehicle around the periphery of the skirt, a necessary byproduct of creating lift.

A flow model that can be used to develop the plenum discharge theory of the hovercraft.

Applying the Bernoulli equation between points 1 and 2, as shown in the figure (above), gives

(2)   \begin{equation*} p_0 + 0 = \dfrac{1}{2} \varrho V_c^2 + p_a \end{equation*}

Solving for the discharge velocity V_c gives

(3)   \begin{equation*} V_c = \sqrt{ \dfrac{2 (p_0 - p_a) }{\varrho} } \end{equation*}

The mass flow rate and volume flow rate, Q, out from around the perimeter of the plenum depends on the ride height, h_c, so that

(4)   \begin{equation*} Q = 2 \pi R_c h_c V_c = 2 \pi R_c h_c \sqrt{ \dfrac{2 (p_0 - p_a) }{\varrho} } \end{equation*}

This latter equation is often modified in accordance with hydraulic theory using an effective discharge coefficient, D_c, i.e.,

(5)   \begin{equation*} Q = 2 \pi D_c R_c h_c \sqrt{ \dfrac{2 (p_0 - p_a) }{\varrho} } \end{equation*}

where D_c < 1 and depends on the wall angle, \theta_c.

The resulting “pumping” power required, P_{\rm req}, to discharge the air around the perimeter gap will be

(6)   \begin{equation*} P_{\rm req} = 2 \pi D_c R_c h_c \left( p_0 - p_a \right) \sqrt{ \dfrac{2 (p_0 - p_a) }{\varrho} } \end{equation*}

which, on rearrangement, gives

(7)   \begin{equation*} P_{\rm req} =2 \pi D_c R_c h_c \left( p_0 - p_a \right)^{3/2} \sqrt{ \dfrac{2 }{\varrho} } \end{equation*}

The using Eq. 1 gives

(8)   \begin{equation*} P_{\rm req} = 2 \pi D_c R_c h_c \left( \dfrac{W}{A_c - A_f} \right)^{3/2} \sqrt{ \dfrac{2 }{\varrho} } \end{equation*}

which, after simplification, gives

(9)   \begin{equation*} P_{\rm req} = 2 R_c h_c \left( \frac{W}{\pi (R_c^2 - R_f^2)} \right)^{3/2} \sqrt{ \frac{2 }{\pi \varrho} } \end{equation*}

without using the discharge coefficient.

Notice that the power required to hover depends on the vehicle’s weight to the power of 3/2 and is also linearly proportional to the hover or ride height, h_c. Additional pressure losses from the intake fan and plenum, as well as frictional losses associated with flow over the ground, can be expected to increase this estimated power by at least 30%. Despite the weight penalty, a power margin of at least 100% would help ensure the hovercraft’s ability to operate under various conditions.

Fan/Plenum Theory

The figure below shows a cross-section of the control volume of a simple hovercraft that uses the pure “plenum” type to lift the vehicle. Assume that the hovercraft has weight W and is of the circular airframe shape with a pressure cushion radius of effective radius R_c. A fan of radius, R_f, which is driven by an engine, draws air from the ambient atmosphere at pressure, p_a, and does work on the air to raise its static pressure by \Delta p, and then to a stagnation pressure, p_0, inside the plenum as the flow velocities approach zero. The resulting differential pressure, i.e., p_0 - p_a acting over the surface of the plenum, becomes the primary source of the resultant lift force on the hovercraft. The other source of lift is the thrust produced by the fan itself, although, in practice, this contribution is smaller and, in the first instance, can be ignored. Again, it can be assumed that the air continuously and steadily escapes from under the hovercraft around the periphery of the plenum.

Flow model that can be used to develop the fan/plenum theory of the hovercraft.

From the conservation of mass, the inlet volume flow rate through the fan must be equal to the exit mass flow rate around the periphery of the plenum, i.e.,

(10)   \begin{equation*} \overbigdot{m} = \varrho v_i \pi R_f^2 = 2 \varrho V_c \pi R_c  h_c \end{equation*}

Therefore, the relationship between the velocity induced by the fan and the exit velocity below the skirt can be expressed as

(11)   \begin{equation*} \dfrac{v_i}{V_c} = \dfrac{ 2 R_c  h_c}{R_f^2} \end{equation*}

The fan does work on the air to increase its static pressure by the amount

(12)   \begin{equation*} \Delta p = p_0 - p_a = \frac{T}{A_f} \end{equation*}

where T is the fan thrust and the ratio T/A_f is the fan disk loading. The fan thrust is obtained by varying its rotational speed as driven by the engine. A gearbox may be installed between the engine and the fan. Notice that lift production from the distribution of the pressure differential in the plenum depends on the disk loading of the fan, i.e., T/A_f. The higher its rotational speed, the higher the disk loading (for a given fan size), so the higher the stagnation pressure in the plenum, the higher the lift on the hovercraft to overcome its weight. Because

(13)   \begin{equation*} \Delta p = \dfrac{W}{\left( A_c - A_f \right)} = \dfrac{W}{\pi \left( R_c ^2 - R_f^2 \right)} \end{equation*}

then

(14)   \begin{equation*} T = \frac{W A_f}{A_c - A_f} = \frac{W R_f^2}{R_c^2 - R_f^2} = W \left( \frac{R_f^2}{R_c^2 - R_f^2} \right) = W \left( \frac{1}{\left( \dfrac{R_c}{R_f} \right) - 1} \right) \end{equation*}

For most hovercraft, the ratio R_c/R_f is greater than 10. It will be apparent that a critical attribute of the hovercraft is the ability to distribute the pressure increment induced by the fan over a relatively large surface area, thereby producing more lift on the vehicle than the fan of a given disk area could produce by itself, i.e., the benefits of a low effective disk or surface loading.

The flow velocity induced by the fan, v_i, depends on the fan disk loading, i.e., for a ducted fan, the relationship is

(15)   \begin{equation*} v_i = \sqrt{ \frac{2 \Delta p}{\varrho}} \end{equation*}

Also, from the conservation of mass, the induced velocity must be

(16)   \begin{equation*} v_i = V_c \left( \dfrac{ 2 R_c  h_c}{R_f^2} \right) = \sqrt{ \dfrac{2 \Delta p }{\varrho} } \left( \dfrac{ 2 R_c  h_c}{R_f^2} \right) \end{equation*}

Therefore, equating terms leads to

(17)   \begin{equation*} v_i = \sqrt{ \dfrac{2 W }{\varrho \pi \left( R_c ^2 - R_f^2 \right)} } \left( \dfrac{ 2 R_c  h_c}{R_f^2} \right) \end{equation*}

The power required P_{\rm req} by the fan (using conversation of energy) is given by

(18)   \begin{equation*} P_{\rm req} = T v_i = \frac{W R_f^2}{R_c^2 - R_f^2} \sqrt{ \dfrac{2 W }{\varrho \pi \left( R_c ^2 - R_f^2 \right)} } \left( \dfrac{ 2 R_c  h_c}{R_f^2} \right) = \frac{2\sqrt{2} W^{3/2} R_c h_c}{\sqrt{\pi \varrho} (R_c^2 - R_f^2)^{3/2}} \end{equation*}

which, after simplification, gives

(19)   \begin{equation*} P_{\rm req} = 2 R_c h_c \left( \frac{W}{\pi (R_c^2 - R_f^2)} \right)^{3/2} \sqrt{ \frac{2 }{\pi \varrho} } \end{equation*}

Notice that the result obtained in Eq. 19 is the same as given previously in Eq. 9 using the plenum discharge theory, as it should be because its derivation is based on the same conservation principles. The power required depends on the hovercraft’s weight to the power of 3/2 and the cushion ride height, h_c. Some fan power increases the static pressure in the plenum, and some of it goes into kinetic energy in the flow. This kinetic energy is lost because it escapes from under the vehicle around its periphery, a necessary byproduct of producing the needed stagnation pressure requirements.

Check Your Understanding #1 – Power required for a plenum hovercraft

A small plenum type of hovercraft has a weight, W, of 4,000 lb. It is of the disk or “saucer” type with a plenum of effective cushion lifting radius, R_c, of 12 ft. The lift fan has a radius of 3 ft. At MSL ISA conditions, estimate how much power is needed for a hover ride height, h_c = 1.0 ft. Assume that the net power system efficiency is 70%.

The hovercraft theory gives the power required as

    \[ P_{\rm req} = 2 \pi R_c h_c \left( \dfrac{W}{A_c - A_f} \right)^{3/2} \sqrt{ \dfrac{2 }{\varrho} } \]

assuming a discharge coefficient of unity. Inserting the numerical values gives

    \[ P_{\rm req} = 2 \pi \times 12.0 \times 1.0 \left( \dfrac{4,000}{\pi ( 12.0^2 - 3.0)^2} \right)^{3/2} \sqrt{ \dfrac{2 }{0.002378} } = 63,334.7~\mbox{ft-lb s$^{-1}$} = 115.15~\mbox{hp} \]

where MSL ISA density is 0.002378 slugs/ft3. If losses give a net system efficiency of 70%, the power required will increase to 115.15/0.70 = 164.5 hp.

Peripheral Jet Theory

The figure below shows the cross-section of a hovercraft that uses the “momentum curtain” type. Again, assume that the hovercraft has weight W and is of the circular “flying saucer” type with an effective pressure cushion of radius, R_c. In this case, the fan works on the air, which flows through the volume between the inner and outer plenums. The resulting flow provides “jet” thrust as it exhausts vertically downward through a plenum gap of width {w}, which then impinges on the ground around the vehicle’s periphery. In this case, the momentum jet reaction augments the lift production on the hovercraft over and above that produced from the stagnation overpressure in the plenum.

Flow model used to develop the peripheral jet or “momentum curtain” effect.

The “momentum” lift force from the peripheral momentum curtain, L_m, depends on the time rate of change of momentum of the flow as it is brought to zero at the surface of the ground or the water. The area of the flow at the exit A_j is given by

(20)   \begin{equation*} A_j = \pi \left( 2 R_c w + w^2 \right) \end{equation*}

which can be approximated as

(21)   \begin{equation*} A_j \approx \pi R_c w \end{equation*}

if {w} is small compared to R_c. Conservation of mass means that the mass flow rate out of the jet equals the mass flow rate into and through the fan, i.e.,

(22)   \begin{equation*} \overbigdot{m} = \varrho v_i A_f = \varrho V_j A_j \end{equation*}

so that

(23)   \begin{equation*} V_j = v_i \left( \frac{ A_f}{A_j} \right) \end{equation*}

The momentum force (lift) augmentation, L_m, on the hovercraft is then

(24)   \begin{equation*} L_m =\overbigdot{m} \sin \theta_c V_j = ( \varrho V_j A_j) \sin \theta_c V_j = \varrho A_j \sin \theta_c \left( \frac{ A_f}{A_j} \right)^2 v_i^2 \end{equation*}

when assuming the jet velocity is turned in a direction parallel to the ground, there are otherwise no other momentum losses. The induced velocity at the fan is

(25)   \begin{equation*} v_i = \sqrt{ \frac{2 \Delta p}{\varrho}} \end{equation*}

so the lift augmentation is

(26)   \begin{equation*} L_m = \varrho A_j \sin \theta_c \left( \frac{ A_f}{A_j} \right)^2  \left( \dfrac{2 \Delta p}{\varrho} \right) = 2 \Delta p \sin \theta_c \left( \dfrac{A_f^2}{A_j} \right) \end{equation*}

The fan does work on the air to increase its static pressure by the amount

(27)   \begin{equation*} \Delta p = \dfrac{T}{A_f} \end{equation*}

Finally, a relatively simple result for the momentum thrust augmentation is obtained, i.e.,

(28)   \begin{equation*} L_m = 2 T \sin \theta_c \left( \dfrac{A_f}{A_j} \right) = 2 T \sin \theta_c \left( \dfrac{R_f^2}{R_c w} \right) \end{equation*}

If it is further assumed, based on the plenum pressure contribution to the lift, that

(29)   \begin{equation*} T = W \left( \dfrac{R_f^2}{R_c^2 - R_f^2} \right) \end{equation*}

then, the final result for the lift from momentum thrust is

(30)   \begin{equation*} L_m = 2 W \left( \dfrac{R_f^2}{R_c^2 - R_f^2} \right) \sin \theta_c \left( \dfrac{R_f^2}{R_c w } \right)^2 = 2 W \left( \dfrac{R_f^4}{R_c w  (R_c^2 - R_f^2)} \right) \sin \theta_c \end{equation*}

Check Your Understanding #2 – Lift augmentation for a “momentum curtain” hovercraft

For the hovercraft assumed in Example #1, estimate the additional lift augmentation using the “momentum curtain” effect. Assume that \theta_c = 75^{\circ} and the curtain jet has a width of {w} = 0.25 feet.

The momentum lift augmenting is given by

    \[ L_m = 2 W \left( \frac{R_f^4}{R_c w (R_c^2 - R_f^2)} \right) \sin \theta_c \]

Inserting the numerical values gives

    \[ L_m = 2 \times 4,000 \left( \frac{3.0^4}{12.0 \times 0.25 \times (12.0^2 - 3.0^2)} \right) \sin 75^{\circ} = 1,545.5~\mbox{lb} \]

Therefore, with all other parameters the same and the same power, the gross weight of the hovercraft could be increased from 4,000 lb to 5,546 lb, about a 30% increase.

Forward Motion of a Hovercraft

Besides lifting fans, a hovercraft must have some form of propulsion to overcome aerodynamic drag and other sources of resistance to move it over the ground or water. There are several drag components, some unique to hovercraft, which must be considered when estimating the performance of such a vehicle in forward motion. In addition to the parasitic drag on the hovercraft, there are contributions from momentum drag, trim drag, and skirt contact drag. For overwater operations, wetting drag and other sources of hull drag from waves may also have to be accounted for. Therefore, the drag buildup for a hovercraft is more complicated than for an airplane because of the need to account for aerodynamic and hydrodynamic effects as well as a variety of vehicle/ground/water interactional effects, which are difficult to qualify.

The use of flexible skirts of various designs has permitted a considerable reduction in ride height, reducing the power required. However, a lower clearance height may increase the contact drag between the skirt and the surface, thereby increasing the drag on the vehicle and the propulsive power. In hovercraft design, there must be a good balance between the power installed for lift and propulsion, affecting the total power requirements for its movement over a given surface at a certain weight and speed. Sufficient thrust and power margins are needed so that performance is not overestimated and the hovercraft can travel over a broad range of terrain and sea states.

Aerodynamic Parasitic Drag

All vehicles will create an aerodynamic parasitic drag when moving through the air, D_a. This drag component can be calculated using the standard drag formula

(31)   \begin{equation*} D_a = \frac{1}{2} \varrho \, V_{\infty}^2 \, A_{\rm ref} \, C_D \end{equation*}

where V_{\infty} is the “airspeed” of the hovercraft over the surface, and C_D is the drag coefficient of the specific shape of the hovercraft. Most hovercraft are not particularly streamlined partly for utility, nor do they need to be because they operate at relatively low speeds compared to airplanes. Drag coefficients for hovercraft shapes have been obtained from wind-tunnel tests and have been found to range in value from 0.25 to 0.4 where A_{\rm ref} is based on the reference of frontal area. However, instead of using drag coefficients and the ambiguity of what is meant by a reference area, it is often useful to represent the drag in terms of equivalent drag area, f_e, where f_e = A_{\rm ref} \, C_D, i.e.,

(32)   \begin{equation*} D_a = \frac{1}{2} \varrho \, V_{\infty}^2 \, f_e \end{equation*}

Skirt Contact Drag

While a hovercraft is designed to have a cushion height h_c and a skirt clearance, there can still be some contact between the rubber skirt and the terrain under certain conditions. Therefore, the manifestation of this contact is a drag component known as the skirt contact drag, D_{\rm sk}. Contact mainly occurs when the hovercraft travels over rough terrain, such as tall grass, vegetation, or brush. This source of drag will also depend on the cushion height, which can be represented as

(33)   \begin{equation*} D_{\rm sk} = C_{\rm sk} \, W \end{equation*}

where C_{\rm sk} is a drag coefficient at a certain cushion height. Notice that skirt contact drag is analogous to a friction force, which depends on weight, not forward speed.

There are no reliable methods to predict this drag component other than semi-empirical rules derived from experiments. However, available results suggest that for average cushion heights, the value of C_{\rm sk} varies from about 0.01 over smooth surfaces such as concrete or short grass to as much as 0.05 for long grass, vegetation, or brush. In some cases, increasing the lifting fan power can increase the cushion height and reduce skirt contact drag.

Momentum Drag

When a hovercraft is moving forward over ground or water, the air exiting around the perimeter of the plenum that produces the “momentum curtain” is redirected by the effects of the airspeed, V_{\infty}. The upshot of this behavior is a form of extra drag known as momentum drag. The equation used to account for the momentum drag is

(34)   \begin{equation*} D_m = \varrho \, Q \, V_{\infty} \end{equation*}

where Q is the volume flow rate through the air cushion system, i.e.,

(35)   \begin{equation*} Q = 2 \pi R_c \, h_c \, V_c \end{equation*}

However, the creation of momentum drag is offset by the increased dynamic pressure at the intake to the lifting fan. While no rigorous methods exist to calculate such effects, this latter effect may reduce as much as 50% of the momentum drag. Compared to other sources of drag on a hovercraft, the momentum drag contribution is relatively small, and its explicit contribution can be neglected in preliminary analyses.

Trim Drag

If the bottom of the hovercraft is not horizontal to the surface, i.e., it is tilted forward or backward, then there will be a horizontal component of the lift force (equal to weight) that will contribute to the drag, i.e.,

(36)   \begin{equation*} D_{\rm tr} = W \sin \theta_t \approx W \theta_t \end{equation*}

where \theta_t is the angle between the cushion base and the surface, which could be nose-down or nose-up. Therefore, trim drag can be a thrust or a drag, depending on the trim state. Because the trim state will also affect skirt contact drag, the weight and balance of the hovercraft must be properly maintained.

Overwater Drag

For overwater operations, there will be additional drag contributions on the hovercraft, including wetting drag and drag from waves. Wetting drag is similar to the effects of skirt drag over the ground, but this drag source depends on the degree of water contact and the volume of water spray hitting the skirt. The factors affecting wetting drag will include the cushion height, vehicle size and shape, and vehicle speed. Empirical data are usually used to estimate overwater drag, which is primarily a hydrodynamic problem. Drag on watercraft from waves, for example, depends on the Froude number and the size and length of the waves, so the effects obtained on drag become a nonlinear function of speed over the water.

Notice that there is a speed where the hydrodynamic drag reaches a maximum, often known as the “hump” speed. This form of drag is usually referred to as wave-making drag. This condition occurs when the length of the wave created by the bow matches the curtain diameter of the hovercraft, which is equivalent to the hull waterline length for a boat. Significant thrust is required to exceed the hump speed, which pilots usually refer to as “getting on the step,” but after that, the drag will decrease as the hovercraft skims over the waves.

Total Drag

The aggregate contribution of all drag sources is shown qualitatively in the figure below. Notice that power is the product of drag and speed; for example, the parasitic power increases with the cube of speed. Overwater operations significantly increase the drag on the vehicle, so the thrust and power required increase commensurately. Therefore, because of the complexity and higher quantitative uncertainties in the drag buildup on a hovercraft, significant power margins are usually introduced into its design at the expense of some higher weight and cost. However, any significant underestimation of the required installed power could have a major impact on the ability of the hovercraft to operate in conditions that it would otherwise be expected.

Representative drag breakdown for a hovercraft operating over land and water.

Check Your Understanding #3 – Estimating the propulsive power for a hovercraft

For the small hovercraft considered in the previous worked examples, estimate the thrust and power required to propel it over tall grass at a speed of 30 knots under MSL ISA conditions. Assume an equivalent parasitic drag area of 30 ft^2, a skirt contact drag coefficient of 0.045, and a net propulsive efficiency of 0.7. Neglect the momentum drag component.

The total drag on the vehicle will comprise the sum of contributions from aerodynamic, momentum, and skirt contact drag. The aerodynamic drag is

    \[ D_a = \frac{1}{2} \varrho\,  V_{\infty}^2 \, f_e  = \frac{1}{2} \times 0.002378 \times (30.0 \times 1.688)^2 \times 30.0 = 91.47~\mbox{lb} \]

The skirt drag is

    \[ D_{\rm sk} = C_{\rm sk} W = 0.045 \times 4,000 = 180.0~\mbox{lb} \]

Therefore, the total drag is

    \[ D = D_a + D_{\rm sk} = 91.47 + 180.0 = 271.47~\mbox{lb} \]

and the power required to generate the needed thrust will be

    \[ P_{\rm req} = \left( \frac{1}{\eta_p}\right) D \, V_{\infty} = 271.47 \times 30.0 \times 1.688/0.7 = 19,638.9~\mbox{ft-lb/s} = 35.71~\mbox{hp} \]

WIGE Vehicle Performance

Flight performance estimates for a WIGE vehicle follow the same fundamental principles as those for an airplane. However, in this case, the challenge is quantifying the additional aerodynamic effects from flow interactions caused by flying near the ground. While various corrections can be applied, the most representative results are probably best obtained from wind tunnel tests using scaled models. The diverse types and sizes (flight weights) of WIGE concepts and sparse empirical data make it difficult to rely on historical trends to establish specific design rules.

The critical issue to account for in predictions is that when a finite wing or lifting surface approaches the ground or another impervious surface, the wing experiences an increase in the lift, as well as a reduction in drag, is observed, which results in an overall improved aerodynamic efficiency. There are two causes of the increase in lift. The first source is the change in the flow field about a wing cross-section, increasing the lower surface pressure and effective angle of attack, sometimes called a ram air effect. The other impact is caused by the laterally outward movement of the wing tip vortices, which manifests as an increase in the effective aspect ratio of the wing and, hence, a reduction in induced drag. The upshot of both effects is an increase in lift and a reduction in drag on the wing, increasing its lift-to-drag ratio and boosting the aircraft’s aerodynamic efficiency. Some WIGE vehicles have been estimated to have lift-to-drag ratios of more than 20, which is higher than many aircraft.

Ram Air Effect

The “ram air” effect typically refers to the increase in stagnation pressure on the lower surface of a wing when flying in proximity to the ground. This beneficial effect results because the airflow patterns around the wing are altered, leading to increased lift. Further improvements in aerodynamic efficiency arise from the lower suction pressure around the airfoil’s leading edge. These two effects on the wing characteristics help allow a WIGE vehicle to maintain flight with better aerodynamic efficiency, reducing power requirements and fuel consumption, the primary effects being illustrated in the figure below.

 

A wing section operating within one chord length of the ground can experience a significant lift augmentation from the so-called “ram air” effect.

The ram air effect depends primarily on the distance between the trailing edge of the wing and the ground, \epsilon, so a wing needs to get within one chord length to experience the benefits. Full-span trailing edge flaps can reduce \epsilon further, as on the ekranoplans, further boosting the ram air effect.

Wing Aspect Ratio Effect

The aspect ratio effect for a wing operating in ground effect pertains to the increase in the effective aspect ratio of the wing by the presence of the ground. Wings with higher aspect ratios (longer and narrower) generally experience less induced drag and are more efficient. Wings with lower aspect ratios can experience a more significant improvement in lift and ground effect efficiency than wings with higher aspect ratios. However, the effects are pronounced for wings of all aspect ratios. The basic principle is illustrated in the figure below, where the ground or other impervious surface causes a lateral outward movement of the wing tip vortices, increasing the effective aspect ratio of the wing.

 

A wing in the presence of an impervious surface causes a lateral outward movement of the wing tip vortices, increasing the effective aspect ratio of the wing and reducing the induced drag.

The induced drag on a wing near a surface can be approximated by the equation

(37)   \begin{equation*} D_i = \frac{1}{2} \varrho_{\infty} \, V_{\infty}^2 S \left( \phi \frac{{C_L}^2}{\pi \, A\!R e} \right) \end{equation*}

One equation to account for the benefits of the surface proximity is the aspect ratio correction factor or “\phi factor” as given by

(38)   \begin{equation*} \phi = \frac{16 \left( \dfrac{h}{b} \right)^2}{1 + 16 \left( \dfrac{h}{b} \right)^2} \end{equation*}

where h/b is the height-to-span ratio of the wing above the surface. Notice that \phi \rightarrow 1 as h/b increases, so the effects are only significant when the wing operates within one wing span. Therefore, the effective aspect ratio of the wing increases in proximity to the surface, as given by

(39)   \begin{equation*} A\!R_{\rm eff} = \frac{A\!R}{\phi} \end{equation*}

Another approximation for the correction factor is that

(40)   \begin{equation*} \phi = \dfrac{3 \pi \epsilon}{2} \end{equation*}

where e is the distance between the trailing edge of the wing and the surface. These simple models are confirmed by the results below, obtained with wings in wind tunnels, suggesting that surface effects can be considered negligible for more than one wing span above the ground.

Line graph representing the measurements of the reduction in drag on a wing operating in ground effect.
Measurements of the reduction in drag on a wing operating in ground effect allow for the determination of a semi-empirical equation (curve fit).

Thrust & Power Requirements

The drag build-up for a WIGE vehicle follows the same principles as those for an airplane when in flight, although hydrodynamic effects must also be considered until the point of takeoff. Hydrodynamic effects associated with wave-making drag are dominant at low speeds and reach a maximum at the “hump” speed. Significant thrust is required to exceed this speed to get “on the step,” but the net drag on the vehicle will decrease markedly when it becomes airborne, as summarized in the figure below. The initial aerodynamic drag is still relatively high because of induced losses but quickly reduces to a minimum as airspeed builds. The drag then builds with increasing airspeed, the vehicle eventually reaching its maximum speed where drag equals the available thrust.

Representative drag buildup for a WIGE vehicle involves both hydrodynamic and aerodynamic contributions.

For steady-level flight where thrust equals drag, then

(41)   \begin{equation*} T = D = \frac{1}{2} \varrho_{\infty} \, V_{\infty}^2 S C_D = \frac{1}{2} \varrho_{\infty} \, V_{\infty}^2 S \left( C_{D_{0}} + \phi \, k \, {C_L}^2 \right) \end{equation*}

The coefficient k is given by

(42)   \begin{equation*} k = \frac{1}{\pi \, A\!R \, e} \end{equation*}

where A\!R is the wing’s aspect ratio and e is Oswald’s efficiency factor. Because in steady flight L = W then

(43)   \begin{equation*} L = \frac{1}{2} \varrho_{\infty} \, V_{\infty}^2 \, S \, C_L = W \end{equation*}

where \varrho_{\infty} is the air density in which the aircraft is flying, S is the reference wing area, and C_L is the total wing lift coefficient (the assumption here is that the wings generate all of the lift). Notice that \varrho_{\infty} = \varrho_0 \, \sigma where the value of \sigma comes from the ISA model, i.e.,

(44)   \begin{equation*} L = W = \frac{1}{2} (\varrho_0 \, \sigma ) \, V_{\infty}^2 \, S \, C_L \end{equation*}

Rearranging this equation, the lift coefficient that needs to be produced on the wing for a given flight speed can be solved for, i.e.,

(45)   \begin{equation*} C_L = \frac{2 W}{(\varrho_0 \, \sigma) \, S \, V_{\infty}^2} \end{equation*}

Therefore, the drag becomes

(46)   \begin{equation*} D = \frac{1}{2} (\varrho_0 \, \sigma) \, V_{\infty}^2 \, S \, C_{D_{0}} + \frac{2 \phi \, k W^2}{(\varrho_0 \, \sigma) \, S \, V_{\infty}^2} \end{equation*}

and where the corresponding power required, P_{\rm req}, is given by

(47)   \begin{equation*} P_{\rm req}  = D \, V_{\infty} = \frac{1}{2} (\varrho_0 \, \sigma) \, V_{\infty}^3 \, S \, C_{D_{0}} + \frac{2 \phi \, k W^2}{(\varrho_0 \, \sigma) \, S \, V_{\infty}} \end{equation*}

The first term in this latter equation (the profile or zero-lift power) becomes dominant at higher airspeeds, and the second (induced power) becomes more prominent at lower airspeeds. Of course, the exact quantitative relationships between power and airspeed depend on the detailed aerodynamics of the vehicle, the characteristics of the engines, and overall propulsive and aerodynamic efficiencies. Treating all of a WIGE vehicle’s intricacies must be considered beyond the scope of this introductory exposition.

Limitations of WIGE Vehicles

Several significant limitations of WIGE vehicles must be noted, as there are for all GEVs. They are specifically designed to operate within half a wing span above the surface, where the ground effect is most pronounced. Beyond this height, the ground effect quickly diminishes, and the efficiency of the vehicle decreases significantly. This issue can also limit the operational flexibility of WIGE vehicles compared to conventional aircraft in that they cannot use airport runways. Indeed, WIGE vehicles need large bodies of water or flat surfaces for takeoff and landing, further restricting their operational envelope and increasing vulnerability to weather conditions such as strong winds and high waves. High sea states associated with water spray and large waves can impose high loads on the wings and fuselage structure. These loads can manifest as structural limitations during take-off and landing in the same manner as a hovercraft. Large quantities of water ingestion into the engines can also cause surging and significantly increase the risk of power loss. Despite these limitations, WIGE vehicles can be viable for maritime surveillance, coastal patrol, and high-speed transportation over limited ranges.

Summary & Closure

Ground Effect (Air) Vehicles (GEVs) offer several operational advancements and potential enhancements to the aviation spectrum. Hovercraft, which is one type of GEV, continues to offer possibilities for many kinds of civil and military applications. The elementary theories and methods discussed in this chapter provide the needed equations to help size hovercraft concepts. Specifically, the results have been derived to relate the fan power to the increase in static pressure to overcome the weight of a hovercraft and raise it to some specified hovering height. The methods can also be used to size the propulsion system. The technical aspects of future hovercraft designs dictate a good balance between aerodynamics, hydrodynamics, and innovative engineering. Despite their versatility, further developments in hovercraft technology are required and will take advantage of ongoing innovations in materials, electric propulsion, and other aerospace technologies. Some hovercraft designs in the future may incorporate hybrid electric/combustion propulsion systems, which may parallel developments being made in the field of aviation.

In recent years, there has been a resurgence of interest in WIGE vehicles, and renewed technical efforts aim to explore their potential for civilian and military purposes further, including transport and maritime patrol. Despite the promising aspects, challenges such as regulatory hurdles and safety concerns continue to temper the adoption of such vehicles for civil use. Nevertheless, ongoing developments suggest that the technology behind WIGE vehicles still has much to offer, with potential applications for the future. However, the enormous technical and financial investments needed to realize WIGE vehicles mean they may not soon materialize for military or commercial purposes.

5-Question Self-Assessment Quickquiz

For Further Thought or Discussion

  • Explain the main components of a hovercraft and how they contribute to its operation.
  • What are the two main principles of lift generation in a hovercraft?
  • Discuss the advantages and disadvantages of using a skirt system in hovercraft design.
  • Describe the challenges involved in maneuvering and controlling a hovercraft.
  • How do hovercraft handle different surface conditions, such as rough water or uneven terrain?
  • Explain the advantages of hovercraft compared to boats and terrestrial vehicles, such as for search and rescue and military operations.
  • Regarding the aviation and maritime spectrum, what might be the advantages and limitations of using WIGE vehicles compared to traditional aircraft and boats?
  • Discuss the challenges of controlling and maneuvering WIG vehicles during takeoffs, turns, and landings.
  • Explain the potential role of WIG vehicles for maritime patrol, coastal surveillance, and transportation.

Other Useful Online Resources

For additional resources on ground effect vehicles, follow up on some of these online resources:

  • Find out more about hovercraft at the Hovercraft Museum.
  • What happened to giant hovercraft?
  • Hovercraft – The ultimate frictionless amphibious machine.
  • The Top 15 awesome hovercraft.
  • SRN4 Hovercraft: UK British Transport History. Video
  • UK passenger hovercraft from Calais, France, to Dover, England. Hoverspeed.
  • Why most hovercraft have disappeared. Video.
  • U.S. Navy’s amphibious hovercraft LCAC. Video.
  • This vehicle looks like an airplane, has a car’s engine, and docks like a boat. Video.

 

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Introduction to Aerospace Flight Vehicles Copyright © 2022 – 2024 by J. Gordon Leishman is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License, except where otherwise noted.