
	Where results make sense

Topic: Swept wing

Related Topics

Wave drag

Transonic

Saab 29

Sonic boom

Boeing 2707

Messerschmitt Me 262

Mach number

Concorde

Soviet Air Force

CCNP

Transsonic

In the News (Tue 17 Nov 09)

Northern Trust

Marvin Harrison

Peter Chernin

Gary Locke

Match Play

Penelope Cruz

Mickey Rourke

AR Rahman

Danny Boyle

Hugh Jackman

	Dictionary : Wing_types
		A small wing called a canard is often attached to the fuselage near the front on this type of aircraft.
		The term "dihedral" is used to describe wings that are angled upward from the fuselage.
		Dihedral is the angle at which the wings are slanted upward from the root of the wing (where it is attached to the fuselage) to the wing tip.
	www.centennialofflight.gov /essay/Dictionary/wing_types/DI98.htm (327 words)

	Swept wing
		A swept-wing is a wing planform used on high-speed aircraft that spend a considerable portion of their flight time in the transonic.
		In their presentation they noted that the wing "thickness" for these calculations was measured along the direction of the airflow, as opposed to along the line of the chord.
		At the wing root, by the fuselage, this has little noticable effect, but as you move towards the tip the airflow is pushed sidewise not only by the wing, but the sidewise moving air beside it.
	www.ebroadcast.com.au /lookup/encyclopedia/sw/Swept-wing.html (1215 words)

	Britain.tv Wikipedia - Wing
		The most common use of wings is to fly by deflecting air downwards to produce lift, but upside-down wings are also commonly used as a way to produce downforce and hold objects to the ground (for example: racing cars).
		Swept wings are wings that are bent back at some angle, instead of sticking straight out from the fuselage.
		Forward-swept wings are high performance wings that are bent forward, the reverse of a traditional swept wing.
	www.britain.tv /wikipedia.php?title=Wing (1170 words)

	Aircraft stall-spin entry deterrent system - Patent 4776542
		The effectiveness of the wing leading-edge droop modification in delaying outboard-wing stall to high angles of attack is caused by vortex flow at the inboard end of the droop, which prevents separated flow from progressing outboard on the wing.
		Wing tip panel 18 is provided with a root chord 20 of substantially the same length as, and is rigidly attached to, the outboard tip chord 22 of wing panel 14.
		The juncture between the main wing panel tip chord 22 and the root chord 20 of the wing tip panel 18 is sealed to preclude any airflow leakage from the lower surface of the wing to the upper surface.
	www.freepatentsonline.com /4776542.html (3415 words)

	Forward Swept Wing, Supersonic Aerodynamics (Site not responding. Last check: 2007-10-26)
		At constant root bending moment, the wing with forward sweep has a slightly higher aspect-ratio, which leads to a further reduction of the profile drag.
		Wing stall starts at the root and proceeds outwards, while on a wing with aft sweep stall unusually starts at the tip and proceeds inwards.
		The use of this wing is mostly confined to experimental fighter aircraft (Grumman X-29A, Sukhoi S 37).
	aerodyn.org /Wings/fsw.html (321 words)

	Forward-Swept Wings
		On the forward swept wing, the air tended to flow inward toward the root of the wing rather than outward toward the wing tip as on the swept-back wing.
		For years the primary purpose for developing forward-swept wings was structural—to allow the wings to be mounted farther back on the fuselage so that their connecting structure did not interfere with anything inside the fuselage (like bombs or people).
		The reverse airflow inward from the wing tip toward the root of the wing did not allow the wing tips and their ailerons to stall at high angles of attack.
	www.centennialofflight.gov /essay/Evolution_of_Technology/foward_sweep/Tech9.htm (1073 words)

	SWING-WING: A History of Variable-Geometry Aircraft - Aerodynamics (Site not responding. Last check: 2007-10-26)
		Essentially, a swept wing "cheats" the oncoming air into behaving as if it were passing over a broader, thinner wing and so the aircraft can travel more swiftly through the air.
		It could also be said that swing wing technology (i.e., its added cost) was at the very least the proverbial "thorn in the side" in the development of aircraft such as the F-111 and the B-1.
		Swing wing aircraft will no doubt continue to be produced where it is prudent and this web site is intended to provide an overview of the technology's history, its successes as well as failures, and, in a small way, a celebration of this unique niche in aviation.
	home.earthlink.net /~p51ace/SwingWing/aerodyn.html (657 words)

	SWING-WING: A History of Variable-Geometry Aircraft - XF10F-1 (Site not responding. Last check: 2007-10-26)
		The original design of the F10F-1 did not have variable swept wings, but had variable incidence wings, the idea being to reduce the angle of attack of the fuselage for landing visibility with a fixed swept wing.
		The flaps were to cause a minor problem, because once the wings were 'swept' the inboard ends of the flaps were slotted into the fuselage, rendering them useless.
		On 16 Apri1 1952, the wings of the XF10F-1 were removed and, together with the rest of the aircraft, they were packed into a USAF Globemaster and shipped to the testing ground.
	home.earthlink.net /~p51ace/SwingWing/xf10f1.html (1067 words)

	NASA - NASA Dryden Fact Sheet - X-29
		Its forward swept wings were mounted well back on the fuselage, while its canards — horizontal stabilizers to control pitch — were in front of the wings instead of on the tail.
		Air moving over the forward-swept wings tended to flow inward toward the root of the wing instead of outward toward the wing tip as occurs on an aft swept wing.
		Wing trailing edge actuators controlling camber are mounted externally in streamlined fairings because of the thinness of the supercritical airfoil.
	www.nasa.gov /centers/dryden/news/FactSheets/FS-008-DFRC.html (1748 words)

	Junkers Ju 287 (Site not responding. Last check: 2007-10-26)
		As an airplane flies through the air, its wing is subjected to a more-or-less random twisting moment exerted by variable aerodynamic forces caused by rapid changes in wind currents or by rapid maneuvers.
		If the wing is swept forward, a small increase in the angle of attack at the tip will increase the lift, causing a twisting moment at the tip, which in turn will cause an increased angle of attack, which will cause still more lift, etc. This causes the aircraft to become seriously unstable.
		The wing of the Ju 287 V2 was similar to that of the V1, but the fuselage was entirely different, being quite similar to that of the propeller-driven Ju 388.
	www.csd.uwo.ca /~pettypi/elevon/baugher_other/ju287.html (1048 words)

	Forward-swept wing - Wikipedia, the free encyclopedia
		Fifty were built; the purpose of the forward swept wing was to allow an unimpeded cabin without a large wing spar passing through it.
		The concept was considered highly impractical until the late 1970s, when DARPA began investigating the use of newer composite materials to strengthen the wings; fly-by-wire technology allowed for the design to be dynamically unstable and therefore highly maneuverable.
		Originally, the F-16 SFW (swept forward wing) was to be the platform for this project, but for mainly political reasons, the Grumman X-29, which used about 16% F-16 components (including the fly-by-wire system), was chosen instead.
	en.wikipedia.org /wiki/Forward-swept_wing (403 words)

	Grumman F9F-6 Cougar
		Conceived as a straightforward derivative of the Panther, the F9F-6 retained the fuselage, vertical tail surfaces, power plant, and undercarriage of the F9F-5 and was fitted with wings swept at 35 degrees at quarter chord and with swept horizontal tail surfaces.
		To compensate for the increase in approach and stalling speeds resulting from the use of swept wings, the chord of the leading-edge slats and that of the trailing-edge flaps were increased and much larger split flaps were fitted beneath the center section.
		The use of an hydraulically-operated 'flying tall' easily cured the longitudinal control deficiency but lateral control remained unsatisfactory until the horn balanced ailerons were replaced by' flaperon/'flaperette' spoilers fitted on the wing upper surface at about 75 per cent of the chord line.
	www.bobjellison.com /f9f_6.htm (671 words)

	Air Force Technology - Su-47 (S-37) Berkut - Experimental Fighter Aircraft
		Su-47 is in a forward swept wing configuration and uses a highly unstable triplane (with three main lifting surfaces) aerodynamic configuration.
		The ailerons - the wing's control surfaces - remain effective at the highest angles of attack, and controllability of the aircraft is retained even in the event of airflow separating from the remainder of the wings' surface.
		The leading-edge root extensions blend smoothly to the wing panels, which are fitted with deflectable slats on the leading edge; flaps and ailerons on the trailing edge.
	www.airforce-technology.com /projects/s37 (758 words)

	ASK DJ Aerotech Question (Site not responding. Last check: 2007-10-26)
		The main culprit for swept wings in this regard is something called the "lift valley" that occurs in the center section of aft-swept wings.
		This is one reason why swept wings often have all sorts of gimcracks and widgets and miscellaneous ironmongery hung all over them such as stall fences, sawtooth leading edges, vortilons, vortex generators, etc., in an attempt to stop the stalled areas from spreading into more critical regions (such as around the ailerons).
		For example, assume we have a 20 degree swept wing with an RG-15 airfoil, and a root Re of 150,000.
	www.djaerotech.com /dj_askjd/dj_questions/sweepwash.html (1934 words)

	Forward swept wing?
		Swept back wings have a certain degree of self stabalizing action as opposed to the swept forward type that requres a large amount of fin area.
		That wing planform is going to need the center of gravity to be located somewhere in the front part of the center pod.
		I've also moved the "fuel tank and wing gear" pods in a little and extended the tips along with some sweep back to restore some of the stability that would be lost to the sweep forward.
	www.rcuniverse.com /forum/m_126816/mpage_2/printable.htm (2442 words)

	Junkers Aircraft of the Twenties
		Wing studies were continued with EF58, which got an elliptic forward swept wing form and EF59 with forward swept wing and nose flaps.
		Its nose section, the forward swept wings and the engine positions are exactly in the position of the V1.
		This wing design of course was directly influenced by the Ju287 design, which Wocke had started at Dessau in 1944 and which was continued 20 years later with the HFB320.
	www.geocities.com /hjunkers/ju_ju287_a1.htm (1509 words)

	NASA Dryden AD-1 Oblique Wing Photo Collection
		The oblique wing could be rotated on its center pivot so that it could be set at its most efficient angle for the speed at which the airplane was flying.
		The oblique wing was the brainchild of NASA aeronautical engineer Robert T. Jones, whose analytical and wind tunnel studies at the NASA Ames Research Center, Moffet Field, California, indicated that an oblique wing, supersonic transport might achieve twice the fuel economy of an aircraft sporting more conventional wings.
		Variable-sweep wings allow an aircraft to take advantage of the lift and handling qualities of a straight wing during the comparatively slow flight of takeoffs and landings, and the reduced drag and the better efficiency of swept-back wings during high speeds and cruise speeds.
	www.dfrc.nasa.gov /gallery/photo/AD-1/index.html (347 words)

	The Swept Wing (Site not responding. Last check: 2007-10-26)
		The whole idea of sweeping an aircraft's wing is to delay the drag rise caused by the formation of shock waves.
		However, in the United States and Great Britain, the concept of the swept wing remained virtually unknown until the end of the war.
		Not to be outdone, the Soviet Union introduced the swept wing in the Mikoyan Mig-15 in 1947.
	www.aviation-history.com /theory/swept-wing.htm (226 words)

	Swept wing - Wikipedia, the free encyclopedia
		The swept wing is used in airplanes that spend a portion of their flight time in the transonic speed range.
		At the wing root, by the fuselage, this has little noticeable effect, but towards the tip the airflow is pushed sidewise not only by the wing, but the sidewise moving air beside it.
		Another concern is the torque applied by the wing to the fuselage, as much of the wing's lift lies behind the point where the wing root connects to the plane.
	en.wikipedia.org /wiki/Swept_wing (1347 words)

	wkasper
		Wing braced from above by kingpost and cables, from below by cables; wing profile by W. Kasper; single-surface.
		The Kasper can be summarized as twin rudders carried on tripod struts at the extremity of each wing in such a way that the rudders are also used as vortex generators and as air brakes.
		Consequently the lift differential on the wing produces a rolling moment in the direction of the actuated rudder.
	www.twitt.org /wkasper.htm (690 words)

	Northrop/Grumman Switchblade aircraft - Above Top Secret Conspiracy Community
		When the wings are fully extended, the plane can fly slowly to drop bombs precisely on their targets or land on short runways.
		When the wings are swept fully forward, the trailing edge of the wing becomes the leading edge, and the Switchblade can dash away at speeds up to Mach 3.
		In the unswept position the wing is approximately orthogonal to a fuselage centerline, while in the full-forward sweep position the wing has approximately a delta wing planform[platform].
	www.abovetopsecret.com /forum/thread77956/pg1 (1434 words)

	The Why Files \| When birds soar: What happens?
		The wings are swept way back, as shown in the diagram.
		Further away, the "hand wing" is flatter on top and extremely sharp on the front.
		The hand wing resembles the wing of a fighter plane, and it is also often swept back -- angled -- toward the rear.
	whyfiles.org /shorties/166bird_wing (866 words)

	Lesson 22b--Airplane Flight
		In addition, L depends on the "angle of attack" between the wing and the air flow, and of course on the size and design of the wing.
		Another force on the wing and on the airplanes is the drag--that is the name given to the air resistance, and it also grows like the square of the velocity.
		Because in a crude approximation, the flow of air over a swept-back wing can be resolved into a component flowing along the wing, not strongly involved in lift and drag, and a component flowing across the wing, perpendicular to it, which acts like the ordinary flow across a wing that is not swept back.
	www-istp.gsfc.nasa.gov /stargaze/Lflight.htm (1559 words)

	Partners in Freedom
		Research on the swept wing as a drag-reducing mechanism for high subsonic and transonic speeds during the late 1930’s and early 1940’s resulted in some of the first conventional aft-swept wing aircraft during World War II.
		Stalls were expected to start at the wing root rather than the tip (in contrast to aft-swept wings), thereby maintaining the effectiveness of outboard ailerons and their contributions to roll control at low speeds.
		The wing rock was a nonlinear phenomenon, in that the model motions were self-initiating and built up to a limited amplitude independent of the magnitude of the initial disturbance.
	oea.larc.nasa.gov /PAIS/Partners/X_29.html (4168 words)

	AAHS Vol. 48 No. 4 - Winter 2003
		The Air Force wanted to conduct flight tests of a swept wing variant of the F-84 parasite as soon as possible, but it would be three years before Republic would produce the first Thunderflashes.
		In 1949, Republic Aviation Corporation in Farmingdale, New York began development of a swept wing version of the F-84 to improve the high-speed performance of the fighter.
		Although the span of the swept wing Thunderstreak was reduced from 36 feet 5 inches to 33 feet 7 inches, the area of its wing was increased from 260 square feet to 325 square feet.
	www.aahs-online.org /BackIssues/v48n4.htm (1833 words)

	Grumman F9F
		To improve slow-speed flight characteristics, the chord line of the wing, when configured with extended leading-edge slats and trailing-edge flaps, was increased.
		The fuselage was lengthened by two feet, the wing root-mounted intakes were extended farther forward, and the wing root fillets were enlarged.
		Large wing fences were found necessary to inhibit span-wise airflow and to preserve lateral control effectiveness.
	www.nasm.si.edu /research/aero/aircraft/grumman_f9f.htm (979 words)

Try your search on: Qwika (all wikis)