Swept-wing - Factbites

Swept-wing - Factbites
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Topic: Swept-wing

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	Swept wing - Wikipedia, the free encyclopedia
		A swept-wing is a wing planform used on high-speed aircraft that spend a considerable portion of their flight time in the transonic.
		The result was a crash program to introduce new swept wing designs, both for fighters as well as bombers.
		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.
	www.wikipedia.org /wiki/Swept_wing (1267 words)

	Stability augmentation system for a forward swept wing aircraft - Patent 4562546
		Forward swept wings of metal are limited in their use due to the static stability phenomenon of divergence at high speed flight conditions.
		A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion.
		Wing 12 is on the right or starboard side of the aircraft while wing 13 is on the left or port side of the aircraft.
	www.freepatentsonline.com /4562546.html (2722 words)

	X-29
		On the forward-swept wing, ailerons remained unstalled at high angles of attack because the air over the forward swept wing tended to flow inward toward the root of the wing rather than outward toward the wing tip as on an aft-swept wing.
		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.
		Wing trailing edge actuators controlling camber are mounted externally in streamlined fairings because of the thinness of the supercritical airfoil.
	www.globalsecurity.org /military/systems/aircraft/x-29.htm (1972 words)

	Forward Swept Wing, Supersonic Aerodynamics
		One production aircraft with swept back wings, the German business jet HFB 320 Hansa, was moderately successful in the 1960s.
		The largest loads occur at the root, while an aft swept wing has a more gradual loading with a maximum lift around mid-span.
		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.
	www.aerodyn.org /Wings/fsw.html (321 words)

	Junkers Ju 287
		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.
		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.
	www.csd.uwo.ca /~pettypi/elevon/baugher_other/ju287.html (1048 words)

	Means for maintaining a desired relationship between roll and yaw stability in a swept-wing aircraft by varying dihedral as a function of lift coefficient - Patent 5078338
		The present invention ties dihedral to the lift coefficient of a swept wing and varies the geometrical dihedral of such wing in relationship to the change in lift coefficient so as to obtain the desired roll-yaw stability throughout the entire flight envelope.
		Movement of the variable dihedral panels changes the geometric dihedral of such wing in direct response to changes in the wing's lift coefficient and this enables one to maintain the overall effective dihedral of the aircraft, and consequently, the rolling moment stability coefficient, relatively constant throughout the entire flight envelope of the aircraft.
		In other words, wing sweep contributes to the total aircraft effective or aerodynamic dihedral, and consequently the roll stability coefficient, and such effective dihedral changes as the lift coefficient of the wing is changed.
	www.freepatentsonline.com /5078338.html (7988 words)

	ch11-3
		The higher performance of the swept-wing Cougar was achieved with about the same thrust as the straight-wing Panther in spite of a drag-producing increase of 35 percent in wing area.
		Later versions of the aircraft incorporated a wing of larger chord, without slats, to decrease the wing thickness ratio and thus increase the critical Mach number; the corresponding 12-percent increase in wing area also increased the lifting capability of the wing and no doubt compensated to some degree for the removal of the leading-edge slats.
		A smaller wing area, wing sweepback, and thinner airfoil sections, together with careful attention to aerodynamic design, were responsible for the large increment in maximum speed between the two types.
	www.hq.nasa.gov /office/pao/History/SP-468/ch11-3.htm (2381 words)

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

	X-28.5
		Ok, I hope to end up with a model with a forward-swept wing that flies.
		Wing is held on with two nylon bolts and two forward pins into a 1/4" ply former in the fuselage.
		The first three inner wing bays use a truss-type shear web, with all the remaining to the tip using a plate-type shearweb.
	www.cs.wisc.edu /~timc/flying/x285.html (1493 words)

	NASA Dryden AD-1 Oblique Wing Photo Collection
		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.
		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.
		Although the oblique wing is still considered a viable concept for large transports, the unpleasant flying characteristics of the AD-1 at extreme wing-sweep angles may have discouraged aircraft designers from adopting this configuration.
	www.dfrc.nasa.gov /gallery/photo/AD-1/index.html (347 words)

	Infinite 35 Degree Swept Wing -- Experiments by Van den Berg et al
		A flow similar to that which occurs on an infinite swept wing should be simulated.
		Infinite 35 Degree Swept Wing -- Experiments by Van den Berg et al
		In order to obtain a test set-up suitable for checking three-dimensional boundary-layer calculation methods, the following requirements were made of the experimental model.
	cfd.me.umist.ac.uk /ercofold/database/test27/test27.html (1068 words)

	GRUMMAN X-29A
		The most easily identified of these, the forward-swept wing (FSW) was combined with advanced materials, a forward mounted elevator (canard) and an electrical flight control system.
		One problem with the new design was that the wings could not be made rigid enough to keep them from bending dangerously at higher speeds.
		In the 1970s, however, composite materials became available, and wing structures could be built that were both lightweight and very rigid.
	www.wpafb.af.mil /museum/modern_flight/mf36.htm (257 words)

	Swept-wing L-39
		The Navy was given the responsibility of investigating the low-speed stability behavior and stalling characteristics of the swept wing.
		Tufts of string were attached to the sweptback wings in order to ascertain the airflow pattern, and a pair of movie cameras were mounted externally behind the cockpit canopy to film the airflow pattern while in flight.
		L-39-2 was later fitted with a completely swept wing of a design planned for the X-2 experimental rocket-powered research aircraft.
	home.att.net /%7Ejbaugher1/p63_11.html (397 words)

	Forward swept wing? : RC Universe! The Ultimate RC forum
		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.
		im a firm beliver on deltas and swept wings the elevator should be in the middle and at the rear, and ailerons at the tips and forwards, that way you avoid tip spins form uneven elevator movement and flap effects.
		The high wing, on the other hand, sees the crossflow hitting it from the top (since the dihedral angle is in the opposite direction on that side), and therfore is pushed down.
	utopia.rcuniverse.com /rcarchive/19/2002/10/3/25919 (5843 words)

	The X-29A,The Forword Swept Wing Jet
		The X-29A is the only jet that only has farward swept wings to this day.
		The forward swept wing jet.It can fly high altitudes and fly very fast.
	capcyberkids.tripod.com /allan/id3.html (70 words)

	A method for the determination of the spanwise load distribution of a flexible swept wing at subsonic speeds
		A method is presented for the determination of the spanwise load distribution of a flexible swept wing at subsonic speed.
		A method for the determination of the spanwise load distribution of a flexible swept wing at subsonic speeds
		The method is based on a relaxation approach utilizing aerodynamic loadings obtained from previously published work (NACA Rep. 921, 1948) based on Weissinger's simplified lifting-surface theory together with simple beam theory.
	naca.larc.nasa.gov /reports/1951/naca-tn-2222 (98 words)

	X-29A Forward Swept Wing Demonstrator
		In flight the compotoe wings change form constantly to facilitate control of the radical airfoil geometry.
		The avionoics are triplex-redundant fly by wire, and continuously monitor the flight envelop in order to properly control the forward canards, wing trailing edges, flaperons, strake flaps, and tail pieces.
		The first supersonic flight of the X-29A occurred on December 1985 with the speed at 1.03 Mach at 40,000 feet.
	www.milnet.com /x-29a.htm (217 words)

	Aircraft Design Information Sources: The Grumman X-29
		Glenn Spacht, "The Forward Swept Wing: A Unique Design Challenge," AIAA Paper 80-1885, August 1980.
		Sue B. Grafton, William P. Gilbert, Mark A. Croom, and Daniel G. Murri, "High Angle-of-Attack Charactreristics of a Forward-Swept Wing Fighter Configuration," AIAA 1th Atmospheric Flight Mechanics Conference, Aug. 1992.
		D.G. Murri, M.A. Croom, and L.T. Nguyen, "High Angle-of-Attack Flight Dynamics of a Forward-Swept Wing Fighter Configuration," AIAA Paper 83-1837, July 1983.
	www.aoe.vt.edu /Mason/ACiX29.html (428 words)

	Title page for ETD etd-09062001-160151
		The purpose of this thesis is to investigate the crossflow and off-the-surface velocity traces on a moderately swept wing at transonic Mach numbers.
		The Investigation of Crossflow Velocity and Off-the-Surface Streamtrace Topology for a Moderately Swept Wing at Transonic Mach Numbers
		This is the range in angle of attack in which a sudden shift in the location of the shock occurs, so it may be postulated that for this wing the flow topology is more sensitive to shock location as opposed to angle of attack.
	scholar.lib.vt.edu /theses/available/etd-09062001-160151 (573 words)

	Swept Wing
		Wing dimensions have been listed, so customers may check for Protectors by Aircraft or by wing dimensions, If you need a Protector not listed we will gladly make it for you.
		White Knight Wing Protectors is Pleased to announce that our Wing Protectors are being used by William "BV" Vargas.
		Extra closures can be added at $5.00 a pair, and a padded 16x7 pocket w/closure for $10.00, may be added to all Protectors.
	www.wingprotectors.com /prod2.htm (610 words)

	Session Dc - Receptivity & Boundary Layer Transition.
		Crossflow instability of a 3-D boundary layer is a common cause for transition in swept wing flows.
		[Dc.06] Secondary Instability and Transition Predition for Swept Wing Boundary Layers
		The boundary-layer flow modified by the presence of finite amplitude crossflow modes is susceptible to high-frequency secondary instabilites, which are believed to harbinger the onset of transition.
	flux.aps.org /meetings/YR97/BAPSDFD97/abs/S3300.html (1625 words)

	Experimental study of the K-regime of breakdown in straight and swept wing boundary layers
		Experimental study of the K-regime of breakdown in straight and swept wing boundary layers
		[BF.001] Experimental study of the K-regime of breakdown in straight and swept wing boundary layers
		Experiments on the stability of three-dimensional boundary layers on the straight and swept airfoils have been conducted.
	flux.aps.org /meetings/YR00/DFD00/abs/S200001.html (232 words)

	Stability augmentation system for a forward swept wing aircraft - United States Patent 4,562,546
		Forward swept wings of metal are limited in their use due to the static stability phenomenon of divergence at high speed flight conditions.
		A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion.
		Wing 12 is on the right or starboard side of the aircraft while wing 13 is on the left or port side of the aircraft.
	xrint.com /patents/us/4562546 (2811 words)

	The Stability of Two-Phase Flow Over a Swept-Wing (ResearchIndex)
		This flow is a model of the boundary layer which forms on a yawed cylinder and can be used as a useful approximation to the air flow over swept wings during heavy rainfall.
		11 the stability of an infinite swept attachment line boundary..
		7 Transition in the infinite swept attachment line boundary la..
	citeseer.ist.psu.edu /626076.html (532 words)

	Review Aerodynamic characteristics of the close-coupled canard as applied to low to-moderate swept wing - Computer Toaster
		Aerodynamic characteristics of the close-coupled canard as applied to low to-moderate swept wing
		Book / Aerodynamic characteristics of the close-coupled canard as applied to low to-moderate swept wing
	computertoaster.com /reviews/asinsearch_B0006XYPKC (71 words)

	Investigation of the Effects of a Nacelle on the Aerodynamic Characteristics of a Swept Wing and the Effects of Sweep on a Wing Alone - Storming Media
		Investigation of the Effects of a Nacelle on the Aerodynamic Characteristics of a Swept Wing and the Effects of Sweep on a Wing Alone
		Abstract: Investigation of the Effects of a Nacelle on the Aerodynamic Characteristics of a Swept Wing and the Effects of Sweep on a Wing Alone
		Investigation of the Effects of a Nacelle on the Aerodynamic Characteristics of a Swept Wing and the Effects of Sweep on a Wing Alone - Storming Media
	www.stormingmedia.us /15/1541/A154183.html (100 words)

	Bibliographie des DLR (LIDO)
		A Model for the Experimental Study of Curvature Effects on Transition of the Boundary Layer on a Swept Wing - Preliminary Results
	www2.dlr.de /lido/SM-ES/1990/ASE9125901251990.html (22 words)

	Show news - Swept-wing UAV tests advance
		The Nishan Mk2TJ is a derivative of the existing Nishan Mk2 delta wing, propeller-driven target system.
		He says the aircraft is now flying with an electro-optic sensor suite with "several hundred hours" of flight trials still planned.
	www.flightinternational.com /FALANDING_175226.htm (204 words)

	NASA - IN-FLIGHT LIFT-DRAG CHARACTERISTICS FOR A FORWARD-SWEPT-WING AIRCRAFT (AND COMPARISIONS WITH CONTEMPORARY AIRCRAFT), NASA-TP-3414, December 1994, DFRC
		The X-29A data (forward-swept wing) are compared with three high-performance fighter aircraft—the F-15C, F-16C, and F/A18.
		Most of the data were obtained near an altitude of 30,000 ft. A representative Reynolds number, for M = 0.9 and a pressure altitude of 30,000 ft, is based on the mean aerodynamic chord.
		The X-29A and its contemporaries have high tran-sonic wave drag and equivalent parasite area compared with aircraft of the 1940s through 1960s.
	www.nasa.gov /centers/dryden/news/DTRS/1994/Bib/H-1913.html (178 words)

	Large-eddy simulation of the flow over a forward-swept wing at high angle of attack. attivita' di ricerca
		Large-eddy simulation of the flow over a forward-swept wing at high angle of attack.
		Large-eddy simulation of the flow over a forward-swept wing at high angle of attack
		Atti di convegni nazionale con revisori articolo in extenso
	virmap.unipi.it /cgi-bin/virmap/vmibo?doc_pubbl:11574028;main;proc (37 words)

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In the News (Thu 8 Jan 09)