Naca

NACA 0012 with modifications?

Airfoil of Supersonigjetwing

1. In 1939, Eastman Jacobs at the NACA in Langley, designed and tested the first laminar flow airfoil sections. These shapes had extremely low drag and the section shown here achieved a lift to drag ratio of about 300.

Modern airplanes have swept wings and so the NACA airfoil system is hard to apply since it it is constantly changing throughout the wing. Even if it was still in use, or another system is in use, the fact is that most companies keep these values extremely confidential since the wing is the most important part of a plane and they dont want other companies copying their airplanes.