Boundary layer control flaps and apparatus thereof

Claim 1

AN AIRCRAFT WING HAVING AN UPPER SURFACE, A LOWER SURFACE, A MIDDLE PORTION AND A GENERALLY SPANWISE EDGE INCLINED AT A SUBSTANTIAL ANGLE TO THE NORMAL DIRECTION OF MOTION OF SAID WING THROUGH THE AIR; AND A SPANWISE DOOR MOUNTED ON SAID WING ADJACENT TO SAID SPANWISE EDGE AND HAVING A FIRST DOOR EDGE GENERALLY PARALLEL TO SAID SPANWISE EDGE AND PIVOTALLY CONNECTED TO SAID WING AT A PIVOTAL AXIS ADJACENT TO SAID SPANWISE EDGE, A DOOR SECOND EDGE GENERALLY PARALLEL TO SAID DOOR FIRST EDGE AND SUPPORTING A BOUNDARY LAYER CONTROL TUBE, AND A DOOR SURFACE BETWEEN SAID DOOR EDGES; SAID DOOR BEING MOUNTED FOR ROTATIONAL MOVEMENT ABOUT SAID PIVOTAL AXIS AND WITH RESPECT TO SAID WING FROM A RETRACTED DOOR POSITION IN WHICH SAID DOOR HAS ITS SURFACE ADAPTED TO GENERALLY CONFORM TO THE LOWER CONTOUR OF SAID WING ADJACENT SAID SPANWISE EDGE AND IS SMOOTHLY FAIRED TO SAID LOWER SURFACE OF SAID WING, WITH SAID TUBE BEING LOCATED SUBSTANTIALLY BETWEEN THE ELEVATION OF UPPER AND LOWER WING SURFACES AND BETWEEN SAID SPANWISE EDGE AND MIDDLE PORTION OF SAID WING, TO AN EXTENDED DOOR POSITION IN WHICH SAID DOOR SURFACE AND TUBE ARE ON THE SIDE OF SAID SPANWISE EDGE OF SAID WING OPPOSITE FROM SAID MIDDLE PORTION OF SAID WING AND SAID BOUNDARY LAYER CONTROL TUBE IS REMOTE FROM SAID UPPER AND LOWER SURFACES OF SAID WING DEFINING A THICKENED AND GENERALLY SPANWISE EDGE PORTION FOR SAID WING.