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.
Exploratory Low-Speed Wind-Tunnel Study of Concepts Designed to Improve Aircraft Stability and Control at High Angles of Attack
1985
73 pages
Report
Keine Angabe
Englisch
Experimental Study of Aircraft Stability Enhancement at High Angles of Attack
British Library Conference Proceedings | 1996
|Experimental Study of Aircraft Stability Enhancement at High Angles of Attack
British Library Online Contents | 1996
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