公开(公告)号：US3471107A

公开(公告)日：1969-10-07

申请号：US3471107D

申请日：1967-02-10

Applicant: SAAB AB

Inventor： ORNBERG KJELL TORSTEN

IPC: B64C5/12 ,  B64C23/00 ,  B64C23/06 ,  B64C3/00 ,  B64C3/04

CPC classification number: B64C23/06 ,  B64C5/12 ,  B64C23/005 ,  Y02T50/162

公开(公告)号：GB1179568A

公开(公告)日：1970-01-28

申请号：GB542767

申请日：1967-02-03

Applicant: SAAB AB

Inventor： ORNBERG KJELL TORSTEN

IPC: B64C5/12 ,  B64C23/00 ,  B64C23/06

Abstract: 1,179,568. Boundary layer control. SAAB AB. 3 Feb., 1967 [11 Feb., 1966], No. 5427/67. Heading F2R. [Also in Division B7] An aircraft delta wing 7 of which the leading edges (of the outer portions for a "double delta" wing) are swept back by between 55 and 70 degrees, having a suction surface 15, over which, during flight are produced on each side of the fore-aft line of symmetry, a pair of co-rotating vortices 11, 12, 111, 211, 311, 411, has a means (e.g. a fin 20 and/or a blown slot 26, 26 1 ) with a further surface intersecting the surface 15, on each side of and parallel to the fore-aft axis, each further surface causing a vortex 18 between the pair of co-rotating vortices, and rotating counter thereto. The co-rotating vortices 111, 211, 311 may be caused by fences 5. The fins 20 may be retractable for supersonic flight by pivoting about an axis in the surface 15 either parallel to or normal to the fore-aft axis. The slots 26, 26 1 may either pass through the wing or be fed by engine air, and may be closable for supersonic flight by either panels slidable in the suction surface or by a fin 20 folding down.

公开(公告)号：FR1511212A

公开(公告)日：1968-01-26

申请号：FR94296

申请日：1967-02-09

Applicant: SAAB AB

Inventor： ORNBERG KJELL TORSTEN

IPC: B64C5/12 ,  B64C23/00 ,  B64C23/06

Abstract: 1,179,568. Boundary layer control. SAAB AB. 3 Feb., 1967 [11 Feb., 1966], No. 5427/67. Heading F2R. [Also in Division B7] An aircraft delta wing 7 of which the leading edges (of the outer portions for a "double delta" wing) are swept back by between 55 and 70 degrees, having a suction surface 15, over which, during flight are produced on each side of the fore-aft line of symmetry, a pair of co-rotating vortices 11, 12, 111, 211, 311, 411, has a means (e.g. a fin 20 and/or a blown slot 26, 26 1 ) with a further surface intersecting the surface 15, on each side of and parallel to the fore-aft axis, each further surface causing a vortex 18 between the pair of co-rotating vortices, and rotating counter thereto. The co-rotating vortices 111, 211, 311 may be caused by fences 5. The fins 20 may be retractable for supersonic flight by pivoting about an axis in the surface 15 either parallel to or normal to the fore-aft axis. The slots 26, 26 1 may either pass through the wing or be fed by engine air, and may be closable for supersonic flight by either panels slidable in the suction surface or by a fin 20 folding down.