Title:
【発明の名称】翼のための前縁渦フラップ
Document Type and Number:
Japanese Patent JPS58500892
Kind Code:
A
Abstract:
A series of flaps (21) along the leading edge of a highly swept-back wing (20) for a supersonic airplane; wherein, the spanwise series of the flaps (21) comprise a double-flap chordwise having fore and aft flap segments (22, 24). When the leading edge double-flap is positioned at a forward and downward angle-of-deflection relative to the wing (20), the fore-flap segment (22) is further positioned at an angle-of-deflection relative to the aft-flap segment (24). This difference in the deflection angles, between the fore-flap segment (22) and the aft-flap segment (24), creates a vortex flow region ahead of the wing leading edge; and this vortex functions to control separation of an upper surface boundary layer airflow, over the remainder of the upper surface of the wing (20). Also, the vortex flow will move in a spanwise direction outboard toward the tip of a swept-back wing (20), while remaining forward or ahead of the upper surface of the aft-flap segment (24). Additional embodiments relate to various other arrangements for creating a leading edge vortex flow to maintain attached flow over the remainder of the upper surface of the wing.
Inventors:
Middleton Wilber-Duff
Paulson Jiyeon Allen
Paulson Jiyeon Allen
Application Number:
JP50242081A
Publication Date:
June 02, 1983
Filing Date:
June 10, 1981
Export Citation:
Assignee:
The Bowing Company
International Classes:
B64C3/50; B64C23/06; (IPC1-7): B64C3/50; B64C23/06
Attorney, Agent or Firm:
Asamura Akira