Editing Delta wing (section)

===Canard delta===
[[File:Eurofighter 9803 2.jpg|thumb|The [[Eurofighter Typhoon]] has a canard delta wing configuration.]]
A lifting-canard delta can offer a smaller shift in the center of lift with increasing Mach number compared to a conventional tail configuration.

An unloaded or free-floating canard can allow a safe recovery from a high angle of attack. Depending on its design, a canard surface may increase or decrease longitudinal stability of the aircraft.<ref>{{Citation |last=Probert |first=B |publisher=NATO |url=http://ftp.rta.nato.int/public//PubFulltext/RTO/EN/RTO-EN-004///$EN-004-19.pdf |title=Aspects of Wing Design for Transonic and Supersonic Combat |url-status=dead |archive-url=https://web.archive.org/web/20110517202722/http://ftp.rta.nato.int/public/ |archive-date=17 May 2011 }}.</ref><ref>{{Citation |publisher=Mach flyg |url=http://www.mach-flyg.com/utg80/80jas_uc.html |title=Aerodynamic highlights of a fourth generation delta canard fighter aircraft |url-status=dead |archive-url=https://web.archive.org/web/20141127200736/http://www.mach-flyg.com/utg80/80jas_uc.html |archive-date=27 November 2014 }}.</ref>

A canard delta foreplane creates its own trailing vortex. If this vortex interferes with the vortex of the main delta wing, this can adversely affect the airflow over the wing and cause unwanted and even dangerous behaviour. In the close-coupled configuration, the canard vortex couples with the main vortex to enhance its benefits and maintain controlled airflow through a wide range of speeds and angles of attack. This allows both improved manoeuvrability and lower stalling speeds, but the presence of the foreplane can increase drag at supersonic speeds and hence reduce the aircraft's maximum speed.