Results of a series of experimental studies regarding the improvement of the maneuverability of fighter aircraft. The applicability of slotted and unslotted leading edge and trailing edge flaps was tested up to the transonic region on a wind tunnel model as a geometrically variable configuration variant. As a geometrically fixed configuration variant, strakes, or high sweepback leading edge modifications, were attached to the basic delta wing at the wing root and were tested in the entire Mach number range of a fighter aircraft. Through a combination of the maneuver aids improvements of more than 100% over the basic wing could be achieved in certain flight ranges. The efficiency of the strake in the range of high angles of attack considerably exceeds that of the flap system. (Author)
Improvement of Maneuverability at High Subsonic Speeds
1974
21 pages
Report
Keine Angabe
Englisch
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