Abstract
Preliminary design data sheets have established criteria defining the geometry of a swept wing that avoids pitch-up-break at low speeds. These criteria limit the aspect ratio and the sweepback of a stable wing thus reducing its efficiency during cruise and limiting its flight critical Mach number. To overcome this limitation, various devices were used with the most notable one being the swing wing (e.g. B-1 & MiG-23). Preliminary tests on a variable aspect ratio wing suggests that localized active flow control that limits the spanwise flow over the upper wing surface, acts as a fluidic fence potentially overcoming the classical design limitations.
Original language | English (US) |
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State | Published - 2017 |
Event | 57th Israel Annual Conference on Aerospace Sciences, IACAS 2017 - Tel Aviv and Haifa, Israel Duration: Mar 15 2017 → Mar 16 2017 |
Other
Other | 57th Israel Annual Conference on Aerospace Sciences, IACAS 2017 |
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Country/Territory | Israel |
City | Tel Aviv and Haifa |
Period | 3/15/17 → 3/16/17 |
ASJC Scopus subject areas
- Aerospace Engineering