Editing Swept wing (section)

===Supersonic flight===
Swept wings on supersonic aircraft usually lie within the cone-shaped shock wave produced at the nose of the aircraft so they will "see" subsonic airflow and work as subsonic wings. The angle needed to lie behind the cone increases with increasing speed, at Mach 1.3 the angle is about 45 degrees, at Mach 2.0 it is 60 degrees.<ref>[http://www.centennialofflight.gov/essay/Theories_of_Flight/supersonic_flow/TH22G2.htm "Supersonic Wing design: The Mach cone becomes increasingly swept back with increasing Mach numbers."] {{webarchive|url=https://web.archive.org/web/20070930032627/http://www.centennialofflight.gov/essay/Theories_of_Flight/supersonic_flow/TH22G2.htm |date=30 September 2007 }} ''Centennial of Flight Commission,'' 2003. Retrieved: 1 August 2011.</ref> The angle of the [[Mach cone]] formed off the body of the aircraft will be at about sin&nbsp;μ = 1/M (μ is the sweep angle of the Mach cone).<ref>Haack, Wolfgang. [http://www.bwl.tu-darmstadt.de/bwl2/akl/downloads/kolloquien/%5bakl09%5d%20-%20heinzerling%20BILDER.pdf "Heinzerling, Supersonic Area Rule" (in German), p. 39.] {{webarchive|url=https://web.archive.org/web/20090327095031/http://www.bwl.tu-darmstadt.de/bwl2/akl/downloads/kolloquien/%5bakl09%5d%20-%20heinzerling%20BILDER.pdf |date=27 March 2009 }} ''bwl.tu-darmstadt.de.''</ref>