Studies have been made on several wing leading-edge modifications applicable at present to single-engine light aircraft, which produce stabilizing vortices at stall and beyond. These vortices have the effect of fixing the stall pattern of the wing such that the various portions of the wing upper surface stall nearly symmetrically. The lift coefficient produced is maintained at a high level to angles of attack significantly above the stall angle of the unmodified wing, and the divergence in roll usually is reduced to a controllable level. It is hypothesized that these characteristics will help prevent inadvertent spin entry after a stall. Results are presented from recent large-scale wind-tunnel tests of a typical light aircraft, both with and without the modifications. The data indicate (hot the static stall and poststall characteristics of this aircraft, in a typical landing-approach condition, are noticeably improved when it suitable leading-edge modification is employed; and also that no appreciable aerodynamic penalties are evident in the normal flight envelope.
Alleviation of Spin-Entry Tendencies through Localization of Wing-Flow Separation
Aircraft Systems and Technology Conference ; 1978 ; Los Angeles, CA, United States
Journal of Aircraft ; 18 , 2
1981-02-01
Sonstige
Keine Angabe
Englisch
Reduction of Stall-Spin Entry Tendencies Through Wing Aerodynamic Design
SAE Technical Papers | 1976
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