Swept wing
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 A B-52 Stratofortress showing wing with a large sweepback angle. |
A swept wing is a wing planform favored for high subsonic jet speeds first investigated in Germany from 1935 onwards until the end of the Second World War. Since the introduction of the MiG-15 and North American F-86 which demonstrated a decisive superiority over the slower first generation of straight-wing jet fighters during the Korean War, swept wings have become almost universal on all but the slowest jets (such as the A-10). Compared with straight wings common to propeller-powered aircraft, they have a "swept" wing root to wingtip direction angled beyond (usually aftward) the spanwise axis. This has the effect of delaying the drag rise caused by fluid compressibility near the speed of sound as swept wing fighters such as the F-86 were among the first to be able to exceed the speed of sound in a slight dive, and later in level flight.
- See also: Wikipedia
- Related: Delta wing, Forward-swept wing, Planform, Sweep theory, Mach number, Theodore von Kármán, Trapezoidal wing
| Swept Wings and Effective Dihedral Swept Wings and Effective Dihedral www.b2streamlines.com/.../EffectiveDihedral.pdf#search=%22swept%20wings%22 - Web |
| The development of swept wings The development of swept wings www.century-of-flight.net/.../Swept%20Wings%20and%20the%20B-47%20Bomber.htm - Web |
| Simple sweep theory math Simple sweep theory math www.desktopaero.com/appliedaero/potential3d/sweeptheory.html - Web |
Gallery for «Swept wing»
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| Advanced math of swept and oblique wings Advanced math of swept and oblique wings www.desktopaero.com/.../OFW_WP_Ch2_v0711.html - Web |
| The L-39 and swept wing research The L-39 and swept wing research home.att.net/~jbaugher1/p63_11.html - Web |
| Sweep theory in a 3D environment Sweep theory in a 3D environment adg.stanford.edu/aa241/drag/sweepncdc.html - Web |
| CFD results showing the 3 dimensional supersonic b... CFD results showing the 3 dimensional supersonic bubble over the wing of an A 320. Another CFD result showing the MDXX and how the shock vanishes close to the fuselage where the aerofoil is more slender adg.stanford.edu/aa241/design/compaero.html - Web |
