This means that the forward sweep design is less apt to suffer from wing tip stalls as the rearward designs are. It also means that the forward sweep aids in low speed stability and handling characteristics (CFC, 2011). Notable aircraft with this design include the Grumman X-29 experimental fighter and the Let-L13 glider (Hallion, 2011).
Technological Impact
Swept wing design changed the course of World War Two and all subsequent wars where aircraft were employed. It also helped to influence the designs of the space race as well as the experimental designs of the 1950's and 1960's that radically shaped future air travel. As it was first experimented with in a relatively meaningful way during World War Two, it has grown to be incorporated in nearly every subsequent aircraft design, especially those that are built for trans-sonic and super-sonic use. Swept wing technology has shaped aviation and aircraft design as much as or more than most other technological innovations. Without this design feature, many aircraft designs would not be functional. Many of the UAV's used in Afghanistan and Iraq, which represent some of the most cutting edge advances in technology employ this design.
References
In Close Ground Proximity at High Subsonic Mach Numbers." Journal of Aerospace Engineering. Vol. 9, No. 1. Pp. 19-26.
Hallion, Richard, P. (2011). "The NACA, NASA, and the Supersonic-Hypersonic
Frontier." NASA. NASA Technical Reports Server. Retrieved 9 Nov.
Platzer, Max F. (2010). "Review of German development of the swept wing 1935-1945, Hans-
Ulrich Meier with contributions from Burghard Ciesla, Hans Foersching, Hans Galleithner, Werner Heinzerling, Bernd Krag, Hans-Ulrich Meier, Helmut Schubert. American Institute of Aeronautics and Astronautics." Progress in Aerospace Sciences, Vol. 47, No. 4. Pp. 304-305.
Centennial Flight Commission (2011). "Supersonic Wing design: The Mach cone becomes increasingly swept back with increasing Mach numbers." Centennial of Flight Commission Homepage. Retrieved: Nov. 1.
Semionov, N.V.; Kosinov, A.D.; and Yermolaev, Y.G. (2010). "Experimental study of stability of supersonic boundary layer on swept wing." Seventh Symposium on Laminar-Turbulent Transition. Vol. 18, No.2. Pp. 379-384.
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