Supercritical wing

A supercritical wing is a kind of wing designed to increase aircraft performance within the transonic speed range. It was invented and patented by Richard Whitcomb at the NASA Langley Research Center in the 1960s and was first tested on the TF-8A Crusader. While the design was initially developed as part of the supersonic transport (SST) project at NASA, it has since been mainly applied to increase the fuel efficiency of many subsonic aircraft.

The wing gets its name from the use of a unique type of airfoil called a supercritical airfoil.

Research aircraft of the 1950s and 60s found it difficult to break the sound barrier, or even reach Mach 0.9, with conventional airfoils. Supersonic airflow over the upper surface of the traditional airfoil induced excessive wave drag and a form of stability loss called mach tuck. Due to the airfoil shape used, supercritical wings experience these problems less severely and at much higher speeds, thus allowing the wing to maintain high performance at speeds closer to mach 1. The supercritical wing is still the number one choice for high-speed subsonic and transonic aircraft from the Airbus A380 to the Boeing F-15 fighter.

In addition to improved transonic performance, the wing's enlarged leading edge gives it excellent high-lift characteristics. As a result, aircraft utilizing a supercritical wing have superior takeoff and landing performance. This makes the supercritical wing a favorite for designers of cargo transport aircraft. A notable example of one such heavy-lift aircraft that uses a supercritical wing is the C-17.