Source+5

"air plane." //britannica//. britannica, nd. Web. 22 Sep. 2010. .

Aerodynamics
An aircraft in straight-and-level unaccelerated flight has four forces acting on it. (In turning, diving, or climbing flight, additional forces come into play.) These forces are lift, an upward-acting force;  drag, a retarding force of the resistance to lift and to the friction of the aircraft moving through the air;  weight, the downward effect that gravity has on the aircraft; and  thrust, the forward-acting force provided by the propulsion system (or, in the case of unpowered aircraft, by using gravity to translate altitude into  speed). Drag and weight are elements inherent in any object, including an aircraft. Lift and thrust are artificially created elements devised to enable an aircraft to fly. Understanding lift first requires an understanding of an airfoil, which is a structure designed to obtain reaction upon its surface from the air through which it moves. Early airfoils typically had little more than a slightly curved upper surface and a flat undersurface. Over the years, airfoils have been adapted to meet changing needs. By the 1920s, airfoils typically had a rounded upper surface, with the greatest height being reached in the first third of the chord (width). In time, both upper and lower surfaces were curved to a greater or lesser degree, and the thickest part of the airfoil gradually moved backward. As airspeeds grew, there was a requirement for a very smooth passage of air over the surface, which was achieved in the laminar-flow airfoil, where the camber was farther back than contemporary practice dictated. Supersonic aircraft required even more drastic changes in airfoil shapes, some losing the roundness formerly associated with a wing and having a double-wedge shape. By moving forward in the air, the wing’s airfoil obtains a reaction useful for flight from the air passing over its surface. (In flight the airfoil of the wing normally produces the greatest amount of lift, but propellers, tail surfaces, and the fuselage also function as airfoils and generate varying amounts of lift.) In the 18th century the Swiss mathematician Daniel Bernoulli discovered that, if the velocity of air is increased over a certain point of an airfoil, the pressure of the air is decreased. Air flowing over the curved top surface of the wing’s airfoil moves faster than the air flowing on the bottom surface, decreasing the pressure on top. The higher pressure from below pushes (lifts) the wing up to the lower pressure area. Simultaneously the air flowing along the underside of the wing is deflected downward, providing a Newtonian equal and opposite reaction and contributing to the total lift. The lift an airfoil generates is also affected by its “angle of attack”—i.e., its angle relative to the wind. Both lift and angle of attack can be immediately, if crudely, demonstrated, by holding one’s hand out the window of a moving automobile. When the hand is turned flat to the wind, much resistance is felt and little “lift” is generated, for there is a turbulent region behind the hand. The ratio of lift to drag is low. When the hand is held parallel to the wind, there is far less drag and a moderate amount of lift is generated, the turbulence smooths out, and there is a better ratio of lift to drag. However, if the hand is turned slightly so that its forward edge is raised to a higher angle of attack, the generation of lift will increase. This favourable increase in the lift-to-drag ratio will create a tendency for the hand to “fly” up and over. The greater the speed, the greater the lift and drag will be. Thus, total lift is related to the shape of the airfoil, the angle of attack, and the speed with which the wing passes through the air. Weight is a force that acts opposite to lift. Designers thus attempt to make the aircraft as light as possible. Because all aircraft designs have a tendency to increase in weight during the development process, modern aerospace engineering staffs have specialists in the field controlling weight from the beginning of the design. In addition, pilots must control the total weight that an aircraft is permitted to carry (in passengers, fuel, and freight) both in amount and in location. The distribution of weight (i.e., the control of the centre of gravity of the aircraft) is as important aerodynamically as the amount of weight being carried. Thrust, the forward-acting force, is opposed to drag as lift is opposed to weight. Thrust is obtained by accelerating a mass of ambient air to a velocity greater than the speed of the aircraft; the equal and opposite reaction is for the aircraft to move forward. In reciprocating or turboprop-powered aircraft, thrust derives from the propulsive force caused by the rotation of the propeller, with residual thrust provided by the exhaust. In a jet engine, thrust derives from the propulsive force of the rotating blades of a turbine compressing air, which is then expanded by the combustion of introduced fuel and exhausted from the engine. In a rocket-powered aircraft, the thrust is derived from the equal and opposite reaction to the burning of the rocket propellant. In a sailplane, height attained by mechanical, orographic, or thermal techniques is translated into speed by means of gravity. Acting in continual opposition to thrust is drag, which has two elements. Parasitic drag is that caused by form resistance (due to shape), skin friction, interference, and all other elements that are not contributing to lift; induced drag is that created as a result of the generation of lift. Parasitic drag rises as airspeed increases. For most flights it is desirable to have all drag reduced to a minimum, and for this reason considerable attention is given to streamlining the form of the aircraft by eliminating as much drag-inducing structure as possible (e.g., enclosing the cockpit with a canopy, retracting the landing gear, using flush riveting, and painting and polishing surfaces). Some less obvious elements of drag include the relative disposition and area of fuselage and wing, engine, and empennage surfaces; the intersection of wings and tail surfaces; the unintentional leakage of air through the structure; the use of excess air for cooling; and the use of individual shapes that cause local airflow separation. Induced drag is caused by that element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it. As the angle of attack increases, so does drag; at a critical point, the angle of attack can become so great that the airflow is broken over the upper surface of the wing, and lift is lost while drag increases. This critical condition is termed the stall. Lift, drag, and stall are all variously affected by the shape of the wing planform. An elliptical wing like that used on the Supermarine Spitfire fighter of World War II, for example, while ideal aerodynamically in a subsonic aircraft, has a more undesirable stall pattern than a simple rectangular wing. The aerodynamics of supersonic flight are complex. Air is compressible, and, as speeds and altitudes increase, the speed of the air flowing over the aircraft begins to exceed the speed of the aircraft through the air. The speed at which this compressibility affects an aircraft is expressed as a ratio of the speed of the aircraft to the speed of sound, called the Mach number, in honour of the Austrian physicist Ernst Mach. The critical Mach number for an aircraft has been defined as that at which on some point of the aircraft the airflow has reached the speed of sound. At Mach numbers in excess of the critical Mach number (that is, speeds at which the airflow exceeds the speed of sound at local points on the airframe), there are significant changes in forces, pressures, and moments acting on the wing and fuselage caused by the formation of shock waves. One of the most important effects is a very large increase in drag as well as a reduction in lift. Initially designers sought to reach higher critical Mach numbers by designing aircraft with very thin airfoil sections for the wing and horizontal surfaces and by ensuring that the fineness ratio (length to diameter) of the fuselage was as high as possible. Wing thickness ratios (the thickness of the wing divided by its width) were about 14 to 18 percent on typical aircraft of the 1940–45 period; in later jets the ratio was reduced to less than 5 percent. These techniques delayed the local airflow reaching Mach 1.0, permitting slightly higher critical Mach numbers for the aircraft. Independent studies in Germany and the United States showed that reaching the critical Mach could be delayed further by sweeping the wings back. Wing sweep was extremely important to the development of the German World War II Messerschmitt Me 262, the first operational jet fighter, and to postwar fighters such as the North American F-86 Sabre and the Soviet MiG-15. These fighters operated at high subsonic speeds, but the competitive pressures of development required aircraft that could operate at transonic and supersonic speeds. The power of jet engines with afterburners made these speeds technically possible, but designers were still handicapped by the huge rise in drag in the transonic area. The solution involved adding volume to the fuselage ahead of and behind the wing and reducing it near the wing and tail, to create a cross-sectional area that more nearly approximated the ideal area to limit transonic drag. Early applications of this rule resulted in a “wasp-waist” appearance, such as that of the Convair F-102. In later jets application of this rule is not as apparent in the aircraft’s planform.

Devices for aerodynamic control
In some flight conditions—descent, preparing to land, landing, and after landing—it is desirable to be able to increase drag to decelerate the aircraft. A number of devices have been designed to accomplish this. These include speed brakes, which are large flat-plate areas that can be deployed by the pilot to increase drag dramatically and are most often found on military aircraft, and  spoilers, which are surfaces that can be extended on the wing or fuselage to disrupt the air flow and create drag or to act in the  same manner as ailerons. Drag can also be provided by extension of the landing gear or, at the appropriate airspeeds, deployment of the flaps and other lift devices. Lift and drag are roughly proportional to the wing area of an aircraft; if all other factors remain the same and the wing area is doubled, both lift and drag will be doubled. Designers therefore attempt to minimize drag by keeping the wing area as small as possible, while enhancing lift with certain types of trailing-edge flaps and leading-edge slats, which have the ability to increase wing area mechanically. (These devices also alter the camber of the wing, increasing both lift and drag.) A passenger in an aft window seat of a modern airliner can observe the remarkable way in which the wing quite literally transforms itself from a smooth, slim, streamlined surface into almost a half-circle of surfaces by the deployment of a formidable array of lift- and drag-inducing devices. Flaps are extensions of the trailing edge of the wing and can be deflected downward as much as 45°. Many flaps effectively increase wing area, adding to lift and to drag. The angle to which the flaps are deployed determines the relative amount of additional lift or drag obtained. At smaller angles, lift is typically increased over drag, while at greater angles, drag is dramatically increased over lift. Flaps come in a wide variety of types, including the simple split flap, in which a hinged section of the undersurface of the trailing edge of the wing can be extended; the Fowler flap, which extends the wing area by deploying on tracks, creating a slotted effect; and the Kreuger flap, which is a leading-edge flap often used in combination with Fowler or other trailing-edge flaps. Various modern proprietary systems of multiple slotted flaps are used in conjunction with leading-edge slats and flaps, all specially designed to suit the flight characteristics of the particular airplane. Leading-edge flaps alter the camber of the wing and provide additional lift; leading-edge slats are small cambered airfoil surfaces arranged near the leading edge of the wing to form a slot. Air flows through the slot and over the main wing, smoothing out the airflow over the wing and delaying the onset of the stall. Leading-edge slots, which can be either fixed or deployable, are spanwise apertures that permit air to flow through a point behind the leading edge and, like the slat, are designed to smooth out the airflow over the wing at higher angles of attack. The deployment of these devices can be varied to suit the desired flight regime. For takeoff and in the approach to  landing, their deployment is generally to provide greater lift than drag. In flight or after touchdown, if rapid deceleration is desired, they can be deployed in a manner to greatly increase drag.

Primary flight controls
All four forces—lift, thrust, drag, and weight—interact continuously in flight and are in turn affected by such things as the torque effect of the propeller, centrifugal force in turns, and other elements, but all are made subject to the pilot by means of the controls.

** Thrust controls **
The pilot controls thrust by adjustment of the control levers for the engine. In an aircraft with a reciprocating engine these can consist of a throttle, mixture control (to control the ratio of fuel and air going to the engine), and propeller control as well as secondary devices such as supercharger controls or water-alcohol injection. In a turbojet engine, the principal control is the  throttle, with auxiliary devices such as water injection and  afterburners. With water injection, a water-alcohol mixture is injected into the combustion area to cool it, which allows more fuel to be burned. With afterburners, fuel is injected behind the combustion section and ignited to increase thrust greatly at the expense of high fuel consumption. The power delivered by reciprocating and  jet engines is variously affected by airspeed and ambient air density (temperature, humidity, and pressure), which must be taken into consideration when establishing power settings. In a turboprop engine, power is typically set by first adjusting the propeller speed with a propeller lever and then adjusting fuel flow to obtain the desired torque (power) setting with the power lever.

** Propellers **
Propellers are basically rotating airfoils, and they vary in type, including two-blade  fixed pitch, four-blade controllable (  variable) pitch, and eight-blade  contrarotating pitch. The blade angle on fixed-pitch propellers is set for only one flight regime, and this restriction limits their performance. Some fixed-pitch propellers can be adjusted on the ground to improve performance in one part of the flight regime. Variable-pitch propellers permit the pilot to adjust the pitch to suit the flight condition, using a low pitch for takeoff and a high pitch for cruising flight. Most modern aircraft have an automatic variable-pitch propeller, which can be set to operate continuously in the most efficient mode for the flight regime. If an engine fails, most modern propellers can be feathered (mechanically adjusted) so that they present the blade edgewise to the line of flight, thereby reducing drag. In large piston engine aircraft, some propellers can be reversed after landing to shorten the landing run. (Jet engines have thrust reversers, usually incorporating a noise-suppression system, to accomplish the same task.)

** Flight simulators **
There are three factors that force the increased use of flight simulators in training: the complexity of larger aircraft, the expense of their operation, and the increased complexity of the air-traffic control environment in which they operate. Modern simulators duplicate aircraft exactly in terms of cockpit size, layout, and equipment. They also duplicate the external environment and create a realistic sense of flying by means of the three-axis motion platform on which they are placed. Perhaps the most important use of flight simulators is to train crews in emergency situations, so that they can experience firsthand situations that could not safely be demonstrated in actual flight training. However, the simulator is also far less expensive than using actual aircraft for routine transition and proficiency training. So realistic is simulator training that airline crews are sometimes qualified on a new aircraft in a simulator prior to ever flying the aircraft itself.

Types of aircraft
There are a number of ways to identify aircraft by type. The primary distinction is between those that are lighter than air and those that are heavier than air.

Heavier-than-air
This type of aircraft must have a power source to provide the thrust necessary to obtain lift. Simple heavier-than-air craft include kites. These are usually a flat-surfaced structure, often with a stabilizing “tail,” attached by a bridle to a string that is held in place on the ground. Lift is provided by the reaction of the string-restrained surface to the wind. Another type of unmanned aircraft is the unmanned aerial vehicle (UAV). Sometimes called drones or remotely piloted vehicles (RPVs), these aircraft are radio-controlled from the air or the ground and are used for scientific and military purposes. Unpowered manned heavier-than-air vehicles must be launched to obtain lift. These include hang gliders, gliders, and sailplanes. Hang gliders are aircraft of various configurations in which the pilot is suspended beneath the (usually fabric) wing to provide stability and control. They are normally launched from a high point. In the hands of an experienced pilot, hang gliders are capable of soaring (using rising air columns to obtain upward gliding movement). Gliders are usually used for flight training and have the capability to fly reasonable distances when they are catapulted or towed into the air, but they lack the dynamic sophistication of sailplanes. These sophisticated unpowered craft have wings of unusually high aspect ratio (that is, a long wing span in proportion to wing width). Most sailplanes are towed to launch altitude, although some employ small, retractable auxiliary engines. They are able to use thermals (currents more buoyant than the surrounding air, usually caused by higher temperature) and orographic lift to climb to higher altitude and to glide for great distances. Orographic lift results from the mechanical effect of wind blowing against a terrain feature such as a cliff. The force of the wind is deflected upward by the face of the terrain, resulting in a rising current of air. Ultralights, which were originally merely hang gliders adapted for power by the installation of small engines similar to those used in chain saws, have matured into specially designed aircraft of very low weight and power but with flying qualities similar to conventional light aircraft. They are intended primarily for pleasure flying, although advanced models are now used for training, police patrol, and other work, including a proposed use in combat. Experimental craft have been designed to make use of human and solar power. These are very lightweight, sophisticated aircraft, designed with heavy reliance on computers and using the most modern materials. Paul MacCready of Pasadena, Calif., U.S., was the leading exponent of the discipline; he first achieved fame with the human-powered //Gossamer Condor//, which navigated a short course in 1977. Two of his later designs, the human-powered //Gossamer Albatross// and the solar-powered //Solar Challenger//, successfully crossed the English Channel. Others in the field have carried on MacCready’s work, and a human-powered helicopter has been flown. Solar-powered aircraft are similar to human-powered types, except that they use solar panels to convert the Sun’s energy directly to power an electric motor.

Civil aircraft
All nonmilitary planes are civil aircraft. These include private and business planes and commercial airliners. Private aircraft are personal planes used for pleasure flying, often single-engine monoplanes with nonretractable landing gear. They can be very sophisticated, however, and may include such variants as: “warbirds,” ex-military planes flown for reasons of nostalgia, ranging from primary trainers to large bombers; “ homebuilts,” aircraft built from scratch or from kits by the owner and ranging from simple adaptations of Piper Cubs to high-speed, streamlined four-passenger transports; antiques and classics, restored older aircraft flown, like the warbirds, for reasons of affection and nostalgia; and aerobatic planes, designed to be highly maneuverable and to perform in air shows. Business aircraft are used to generate revenues for their owners and include everything from small single-engine aircraft used for pilot training or to transport small packages over short distances to four-engine executive jets that can span continents and oceans. Business planes are used by salespeople, prospectors, farmers, doctors, missionaries, and many others. Their primary purpose is to make the best use of top executives’ time by freeing them from airline schedules and airport operations. They also serve as an executive perquisite and as a sophisticated inducement for potential customers. Other business aircraft include those used for agricultural operations, traffic reporting, forest-fire fighting, medical evacuation, pipeline surveillance, freight hauling, and many other applications. One unfortunate but rapidly expanding segment of the business aircraft population is that which employs aircraft illegally for transporting narcotics and other illicit drugs. A wide variety of similar aircraft are used for specialized purposes, like the investigation of thunderstorms, hurricane tracking, aerodynamic research and development, engine testing, high-altitude surveillance, advertising, and police work. Commercial airliners are used to haul passengers and freight on a scheduled basis between selected airports. They range in size from single-engine freight carriers to the Boeing 747 and in speed from below 200 miles per hour to supersonic, in the case of the Anglo-French Concorde, which was in service from 1976 to 2003.

Wing types
Aircraft can also be categorized by their configurations. One measure is the number of wings, and the styles include monoplanes, with a single wing (that is, on  either side of the fuselage);  biplanes, with two wings, one atop the other; and even, though rarely, triplanes and quadplanes. A tandem-wing craft has two wings, one placed forward of the other. The wing planform is the shape it forms when seen from above. Delta wings are formed in the shape of the Greek letter delta (Δ); they are triangular wings lying at roughly a right angle to the fuselage. The supersonic Concorde featured delta wings. Swept wings are angled, usually to the rear and often at an angle of about 35°. Forward swept wings also are used on some research craft. Some aircraft have wings that may be adjusted in flight to attach at various angles to the fuselage; these are called variable incidence wings. Variable geometry (swing) wings can vary the sweep (i.e., the angle of a wing with respect to the plane perpendicular to the longitudinal axis of the craft) of their wings in flight. These two types have primarily military applications, as does the oblique wing, in which the wing is attached at an angle of about 60° as an alternative to the standard symmetrical wing sweep. Another configuration limited to military craft is the so-called flying wing, a tailless craft having all its elements encompassed within the wing structure (as in the Northrop B-2 bomber). Unlike the flying wing, the lifting-body aircraft (such as the U.S. space shuttle) generates lift in part or totally by the shape of the fuselage rather than the wing, which is severely reduced in size or altogether absent.

Propulsion systems
The engines used to provide thrust may be of several types.

** Jet engines **
The gas turbine engine has almost completely replaced the reciprocating engine for aircraft propulsion. Jet engines derive thrust by ejecting the products of combustion in a jet at high speed. A turbine engine that passes all the air through the combustion chamber is called a turbojet. Because its basic design employs rotating rather than reciprocating parts, a turbojet is far simpler than a reciprocating engine of equivalent power, weighs less, is more reliable, requires less maintenance, and has a far greater potential for generating power. It consumes fuel at a faster rate, but the fuel is less expensive. In simplest terms, a jet engine ingests air, heats it, and ejects it at high speed. Thus in a turbojet, ambient air is taken in at the engine inlet (induction), compressed about 10 to 15 times in a compressor consisting of rotor and stator blades (compression), and introduced into a combustion chamber where igniters ignite the injected fuel (combustion). The resulting combustion produces high temperatures (on the order of 1,400 to 1,900 °F [760 to 1,040 °C]). The expanding hot gases pass through a multistage turbine, which turns the air compressor through a coaxial shaft, and then into a discharge nozzle, thereby producing thrust from the high-velocity stream of gases being ejected to the rear (exhaust). A turbofan is a turbine engine having a large low-pressure fan ahead of the compressor section; the low-pressure air is allowed  to bypass the compressor and turbine, to mix with the jet stream, increasing the mass of accelerated air. This system of moving large volumes of air at a slower speed raises efficiency and cuts both fuel consumption and noise. A turboprop is a turbine engine connected by a reduction gearbox to a propeller. Turboprop engines are typically smaller and lighter than a piston engine, produce more power, and burn more but cheaper fuel. Propfans, unducted fan jet engines, obtain ultrahigh bypass airflow using wide chord propellers driven by the jet engine. Rockets are purely reactive engines, which usually use a fuel and an oxidizing agent in combination. They are used primarily for research aircraft and for launching the space shuttle vehicles and satellites. A ramjet is an air-breathing engine that, after being accelerated to high speeds, acts like a turbojet without the need for a compressor or turbine. A scramjet (supersonic combustion ramjet) is an engine designed for speeds beyond Mach 6, which mixes fuel into air flowing through it at supersonic speeds; it is intended for hypersonic aircraft.

** Engine placement **
Aircraft types can also be characterized by the placement of their power plants. An aircraft with the engine and propeller facing with the line of flight is called a tractor type; if the engine and the propeller face opposite the line of flight, it is a pusher type. (Both pusher propellers and canard surfaces were used on the Wright Flyer; these have now come back into vogue on a number of aircraft. Canards are forward control surfaces and serve to delay the onset of the  stall. Some aircraft also have forward wings, which provide lift and delay the stall, but these are not control surfaces and hence not canards.) Jet engines are variously disposed, but the most common arrangement is to have them placed underneath the wing in nacelles suspended on pylons or placed on stub fixtures at the rear of the fuselage. Supersonic and hypersonic aircraft are usually designed with the engine as an integral part of the undersurface of the fuselage, while in some special military stealth applications, the engine is entirely submerged within the wing or fuselage structure.

Early technology
For reasons of availability, low weight, and prior manufacturing experience, most early aircraft were of wood and fabric construction. At the lower speeds then obtainable, streamlining was not a primary consideration, and many wires, struts, braces, and other devices were used to provide the necessary structural strength. Preferred woods were relatively light and strong (e.g., spruce), and fabrics were normally linen or something similarly close-weaved, not canvas as is often stated. As speeds advanced, so did structural requirements, and designers analyzed individual aircraft parts for both strength and wind resistance. Bracing wires were given a streamlined shape, and some manufacturers began to make laminated wood fuselages of monocoque construction (stresses carried by the skin) for greater strength, better streamlining, and lighter weight. The 1912 record-setting French Deperdussin racers, the German Albatros fighters of World War I, and the later American Lockheed Vega were among the aircraft that used this type of construction. Aircraft made of wood and fabric were difficult to maintain and subject to rapid deterioration when left out in the elements. This, plus the need for greater strength, led to the use of metal in aircraft. The first general use was in World War I, when the Fokker aircraft company used welded steel tube fuselages, and the Junkers company made all-metal aircraft of dual tubing and aluminum covering. During the period from 1919 through 1934, there was a gradual trend to all-metal construction, with some aircraft having all-metal (almost always of aluminum or aluminum alloy) structures with fabric-covered surfaces, and others using an all-metal monocoque construction. Metal is stronger and more durable than fabric and wood, and, as the necessary manufacturing skills were developed, its use enabled airplanes to be both lighter and easier to build. On the negative side, metal structures were subject to corrosion and metal fatigue, and new procedures were developed to protect against these hazards. A wide variety of aluminum alloys were developed, and exotic metals like molybdenum and titanium were brought into use, especially in vehicles where extreme strength or extraordinary thermal resistance was a requirement. As aircraft were designed to operate at Mach 3 (three times the speed of sound) and beyond, a variety of techniques to avoid the effects of aerodynamic heating were introduced. These include the use of fuel in the tanks as a “heat sink” (to absorb and dissipate the generated heat), as well as the employment of exotic materials such as the advanced carbon-carbon composites, silicon carbide ceramic coatings, titanium-aluminum alloys, and titanium alloys reinforced with ceramic fibres. Additionally, some designs call for the circulation of very cold hydrogen gas through critical areas of aerodynamic heating. ARTICLE Additional Reading The basic elements of flying are treated in //Pilot’s Handbook of Aeronautical Knowledge//, rev. ed. (1986), prepared by the U.S. Federal Aviation Administration; Richard L. Taylor, //Understanding Flying// (1977, reissued 1987), covering both human and mechanical aspects of the process; and Richard von Mises , //Theory of Flight// (1945, reissued 1959; originally published in German, 4th ed., 1936), rather technical but comprehensive in coverage. Walter J. Boyne, //The Smithsonian Book of Flight// (1987), is a historical treatment of a wide variety of aviation topics for the general reader. George Geoffrey Smith, //Gas Turbines and Jet Propulsion//, 6th ed., rev. and enlarged by F.C. Sheffield (1955), explains the functions of the turbine jet engine; Bill Gunston , //World Encyclopaedia of Aero Engines//, 2nd ed. (1989), discusses a wide range of engines in historical context; L.J.K. Setright, //The Power to Fly: The Development of the Piston Engine in Aviation// (1971), is a history of this particular type of engine; and W.H. Deckert and J.A. Franklin , //Powered-Lift Aircraft Technology// (1989), is a short overview, prepared by the National Aeronautics and Space Administration, of aircraft that have the capability to vary in flight the direction of the force of the propulsive system. Darrol Stinton, //The Design of the Aeroplane: Which Describes Common-Sense Mechanics of Design as They Affect the Flying Qualities of Aeroplanes Needing Only One Pilot// (1983), is useful for understanding the broader aspects of aircraft design; and Edward H. Heinemann , Rosario Rausa , and K.E. Van Every , //Aircraft Design// (1985), surveys the more sophisticated elements of design with a minimum of mathematics. An insightful look into the incremental steps in the refinement of aircraft design over the years is offered in Laurence K. Loftin, Jr., //Quest for Performance: The Evolution of Modern Aircraft// (1985). Descriptions, illustrations, and specifications of aircraft of a number of countries are provided by //Jane’s All the World’s Aircraft// (annual). For the history of aviation, see C.H. Gibbs-Smith, //Flight Through the Ages: A Complete Illustrated Chronology from the Dreams of Early History to the Age of Space Exploration// (1974); L.T.C. Rolt , //The Aeronauts: A History of Ballooning, 1783–1903// (1966, reissued 1985); Carl Solberg , //Conquest of the Skies: A History of Commercial Aviation in America// (1979); R.E.G. Davies , //A History of the World’s Airlines// (1964); and John Toland , //Ships//