Oblique Wings
These results suggested to R.T. Jones that obliquely-swept wings would be
the ideal shape for supersonic aircraft wings. He first proposed the concept
in the 1940's and flew flying wing models at the first ICAS meeting in Madrid
in 1958. A great deal of work has been done since on oblique wing aircraft
including design work by Boeing, General Dynamics, and Lockheed, wind tunnel
testing and analysis by NASA, and flight testing of models and piloted aircraft.
The picture below shows the AD-1 low speed oblique wing demonstrator.
Although one of the principal advantages involves reduced supersonic wave
drag, the concept has other merits.
When compared to an aircraft with symmetric variable sweep (such as the
B-1 or F-111), the oblique wing has little change in the aerodynamic center
position. This keeps the stability at reasonable levels and avoids large
trim changes or complex fuel-pumping schemes.
In addition, several structural advantages have been suggested, especially
for variable-sweep aircraft: bending loads on the pivot are avoided, only a single
pivot is required, the actuator loads are reduced, and the straight carry-through
structure reduces weight in other portions of the aircraft.
An all-wing version of the oblique wing was first proposed by G. H. Lee
in 1962. The idea has been revived with the advent of active control systems
and a recent artist concept of the oblique flying wing is shown below.
Despite several questions about stability and control, this concept can be made to
fly as illustrated in this 4MB video clip of the first flight of an
oblique all-wing testbed aircraft.