A method for localizing wing flow separation at stall to alleviate spin entry tendencies
Author:
Affiliation:
1. NASA, Ames Research Center, Moffett Field, Calif.
2. Michigan, University, Ann Arbor, Mich.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1978-1476
Cited by 9 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. CFD evaluation of the effects of stall control devices and transition tapes on stall behavior of airplanes;32nd AIAA Applied Aerodynamics Conference;2014-06-13
2. An experimental study of droop leading edge modifications on high and low aspect ratio wings up to 50 deg angle of attack;11th Applied Aerodynamics Conference;1993-08-09
3. Wing leading-edge droop/slot modification for stall departure resistance;Journal of Aircraft;1991-07
4. Large-scale vortex-lattice model for the locally separated flow overwings;AIAA Journal;1982-12
5. Experimental Investigation of a Wing with Controlled Midspan Flow Separation;Journal of Aircraft;1982-06
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