Patent ID: 9463870
Filing Date: 2016-10-11
CPC Classification: B64C,Y02T

Claim Text:
1. A method of operating an aerodynamic structure comprising a leading edge, a trailing edge and series of 3-D shock bumps extending from a surface of said structure, wherein the aerodynamic structure has a fifty percent chord line half way between the leading edge and the trailing edge, the fifty percent chord line has a first angle of sweep, each of the 3-D shock bumps have an apex positioned towards the trailing edge and aft of the fifty percent chord line, and the 3-D shock bumps are distributed along a line with a mean angle of sweep which is less than the first angle of sweep of the fifty percent chord line, wherein the method comprises: flying the aerodynamic structure at a speed sufficient to form a shock on the wing, and perturbing the shock at the surface with the series of 3-D shock bumps.