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This question asks about the benefits of an oblique wing over a delta wing, but I am more interested in the benefits of an oblique wing compared to a swing wing.

Wikipedia states:

This is a variation on the classic swing-wing design, intended to simplify construction and retain the center of gravity as the sweep angle is changed.

But I'm pretty sure there are a lot more advantages or disadvantages, in terms of stalling behavior (forward swept side inboard first, aft swept side outboard first), aircraft control etc.

Related: What are the advantages of a forward-swept wing over a rearward-swept wing?

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Advantages of an oblique wing over swing wings:

  • Low wave drag due to favorable volume distribution over length.
  • Lower structural mass. The hinge of a swing wing is heavy!
  • No shift in the center of lift (if the sweep angle is higher than the Mach angle). A swing wing experiences a severe shift in the center of lift.

Disadvantages of an oblique wing over a swing wing:

  • One wing is swept forward, the other aft. This is no problem in straight flight, but when maneuvering, it will behave in odd ways because the axes of its inertial system are not aligned with the direction of flight.
  • Aeroelasticity: Gust response when flying oblique will include a roll answer, because the forward-swept wing will twist to a higher angle of attack in a positive gust, increasing lift, whereas the backward swept wing will twist to a lower angle of attack (aeroelastic washout).
  • Wing-airframe integration is complex, and the wing needs to be on top of the fuselage (unless you have a flying wing; then the disadvantage is a really small payload volume). The swing wing needs much space for the hinge, spar carry-through and actuation, but can be placed anywhere you like.

Note that all other effects which plague the forward-swept wing apply here, too, but only on one side. The effect of boundary layer thickening will only happen on the backward-swept side, so changing the angle of attack will already create a rolling moment. The oblique wing will only behave normally when set at a sweep angle of 0°.

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    $\begingroup$ Good answer! About your second argument, wouldn't the hinge (or pivot) of an oblique wing also be very heavy? $\endgroup$ – ROIMaison Aug 20 '15 at 12:06
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    $\begingroup$ @ROIMaison: This is in comparison to a swing wing. Of course, a straight carry-through without hinge is the lightest solution. But the oblique wing needs only one hinge in the interface between fuselage and wing. I changed "low" to "lower"; now it makes more sense. $\endgroup$ – Peter Kämpf Aug 20 '15 at 12:14
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The oblique wing and the swing wing aim to reduce the drag over a wide range of speeds by changing the wing sweep. While the swing wing rotates a part of the wing to achieve this, the oblique wing rotates the whole wing.

The first production aircraft with variable sweep wings was the F111 Aardvark, while the most famous one is the F-14 Tomcat.

F 14 prototypes in flight
"F-14 Tomcat prototypes in flight c1972" by U.S. Navy - U.S. Navy National Museum of Naval Aviation photo No. 2011.003.301.027. Licensed under Public Domain via Commons.

However, the only full sized aircraft to be produced with an oblique or pivot wing was the NASA AD-1, which was strictly an experimental aircraft.

AD 1
"AD-1 ObliqueWing 60deg 19800701" by NASA - http://www1.dfrc.nasa.gov/Gallery/Photo/AD-1/HTML/ECN-15846.html. Licensed under Public Domain via Commons.

A comparison between the two can be made like this:

  1. Aerodynamics: The oblique wing is much more refined aerodynamically compared to the swing wing and had lesser drag. In fact the AD-1 was designed to be as close to the optimal for all the flight regimes. Also, the aircraft was designed to have an elliptical lift distribution to reduce induced drag. on the other hand, the variable geometry aircraft did not offer any significant advantages over fixed wing baseline aircraft.

However, the asymmetric stall of the oblique wing aircraft would cause problems as one side of the wing is swept forwards and the other side is swept towards the rear.

  1. Structure: The hinge was arguably the most critical structural part in variable sweep wing aircraft. The hinge should not only have a very high reliability, but also have the capacity to bear the high aerodynamic loads.

Panavia Tornado Hinge
"Tornado variable sweep wing Manching" by Sovxx - Own work. Licensed under CC BY-SA 3.0 via Commons.

In this case, the swing wing aircraft are better off compared to the oblique wing aircraft as the amount of load on the hinge is significantly lower.

For example, the oblique wing hinge has to take not only the weight of the entire aircraft wing (the swing wing aircraft typically rotate only a part of the wing), but also the entire fuel load (the amount of fuel carried in the variable part of the wing is significantly small). Also, the hinge should take the load of the control system too.

  1. Handling and Controls: The handling of the swing wing aircraft have been brought closer to the fixed wing aircraft over time. However,the handling qualities of AD-1 was found to be poor, with unusual trim requirements and inertial coupling affecting the aircraft negatively.

For instance, the AD-1 required about 10° of bank in order to trim the aircraft with no sideslip at 60° wing sweep.The aircraft also experienced pitch-roll coupling and the associated aeroelastic effects made for unpleasant handling qualities above 45 degrees sweep.

One advantage of the oblique wing aircraft is that the center of lift and mass doesn't move as the wings are swept. This happens in the swing wing aircraft and the control system is complicated

  1. Engine and payload In case of swing wing aircraft, the engines can be mounted in the fuselage (like F-14) or in the (fixed part of) wing itself (like B-1). In case of the oblique wing aircraft, locating the engines anywhere except the fuselage is effectively ruled out.

In case of military aircraft, use of hardpoints in the variable point of the wing is limited (for one thing, this will increase the load on the hinge). This is a much more serious problem for oblique wing aircraft as this limits the payload that could be carried.

However, the main reason for the lack of further development of oblique wing aircraft is their unusual and unpleasant control qualities.

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    $\begingroup$ The hinge of a swing wing needs to transmit lift and bending moment, while the central hinge of the oblique wing only needs to transmit lift. How can the oblique wing hinge be heavier than two swing wing hinges? $\endgroup$ – Peter Kämpf Aug 22 '15 at 18:12
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The oblique wing has been studied as yet another way to improve the speed envelope and/or fly more efficiently at higher airspeed. It was intended for long distance cruising application, but never was able to make any headway against what is universally seen in modern designs, change of camber.

It is honestly surprising that even rudimentary slats have not found their way into mainstream application yet for recreational aircraft, as combined with flaps, they produce huge amounts of lift, enabling very low take off and landing speeds. Probably one of the finest examples of a successful light aircraft design that employed slats was the Fiesler Fi 156 Storch. Slats, along with slotted "doppel wing" flaps make the Storch an outstanding STOL aircraft, making them retractable would enable better cruise performance, as airliners do.

Changing wing geometry, as seen in the B1 bomber, is still useful in the application of providing a wider range of ALTITUDES for high speed cruise. The B1 can go high with wings extended, or low with wings back. Survivability in these times favors going low.

The oblique concept did improve high speed cruise efficiency, but never found an application niche where it was clearly better than changing camber or sweeping both wings back. It did not sell.

There is one possibility that may be of interest. That would be FULLY rotating the wing parallel to the fuselage and flying on the tail and canard only. In the days of sail, in high winds, the mainsail was dropped, and the fore and rear sails were used only. This was referred to as sailing "jib and jigger".

The reduced wing area would lower lift and drag considerably, allowing for much higher, perhaps supersonic speeds.

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