Aircraft wing system having zero induced drag

Claim 1

IN COMBINATION, FIRST MEANS DEFINING A FIRST FLUID CONTACT SURFACE OF FINITE SPANWISE DIMENSIONS AND OVER WHICH A MAIN FLUID FLOWS FROM A LEADING TO A TRAILING EDGE, TO TRAIL OFF THE TRAILING EDGE, SECOND MEANS DEFINING A SECOND FLUID CONTACT SURFACE HAVING THE SAME LEADING AND TRAILING EDGES AS SAID FIRST MEANS AND SEPARATING THE FLUID, SO THAT A SECOND MAIN FLOW PORTION FLOWS UNDER THE SECOND MEANS FROM THE LEADING EDGE TO TRAIL OFF FROM THE TRAILING EDGE, AT LEAST ONE OF SAID FIRST AND SECOND MEANS BEING CURVED TO PRODUCE LIFTING FORCE FOR SUSTAINING SAID FIRST AND SECOND MEANS IN THE FLUID, THERE RESULTING A FIRST FLOW COMPONENT ALONG SAID FIRST MEANS IN A FIRST SPANWISE ORIENTED DIRECTION AND SECOND COMPONENT ALONG THE SECOND MEANS IN THE RESPECTIVE OPPOSITE DIRECTION, AND THIRD MEANS STRUCTURALLY COMBINED WITH SAID FIRST AND SECOND MEANS FOR SUBSTANTIALLY ELIMINATING SAID FIRST AND SECOND FLOW COMPONENTS IN BOTH OF THE MAIN FLOWS ALONG SUBSTANTIALLY THE ENTIRE SPAN AFT OF SAID FLUID CONTACT SURFACES.