NASA-CR-176615
Exploratory low-speed wind-tunnel study of concepts designed to improve aircraft stability and control at high angles of attack
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Abstract:
A wind tunnel investigation of concepts to improve the high angle-of-attack stability and control characteristics of a high performance aircraft was conducted. The effect of vertical tail geometry on stability and the effectiveness of several conventional and unusual control concepts was determined. These results were obtained over a large angle-of-attack range. Vertical tail location, cant angle and leading edge sweep could influence both longitudinal and lateral-directional stability. The control concepts tested were found to be effective and to provide control into the post stall angle-of-attack region.
Author(s):
D.E. Hahne
Indexed under:
- None
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