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http://dx.doi.org/10.5139/JKSAS.2015.43.3.224

An Experiment Study on Sideslip Angle Effect of Lambda Wing Configuration  

Shim, HoJoon (Korea Advanced Institute of Science and Technology)
Park, Seung-O (Korea Advanced Institute of Science and Technology)
Oh, Se-Yoon (Agency for Defense Development)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.43, no.3, 2015 , pp. 224-231 More about this Journal
Abstract
An experimental study on aerodynamic coefficients of a lambda wing configuration was performed at the low speed wind tunnel of Agency for Defense Development. The main purpose of this study was to investigate the effects of sideslip angle on various aerodynamic coefficients. In the case of $0^{\circ}C$ sideslip angle, nose-up pitching moment rapidly increases at a specific angle of attack. This unstable pitching moment characteristic is referred to as pitch break or pitch up. As the sideslip angle increases, the pitch break is found to be generated at a higher angle of attack. Rolling moment is found to show similar behavior pattern to 'pitch break' style with angle of attack at non-zero sideslip angles. This trend gets severer at greater sideslip angles. Yawing moment also shows substantial variation of the slope and the unstable directional stability with sideslip angles at higher angles of attack. These characteristics of the three moments clearly implies the difficulty of the flight control which requires efficient control augmentation system.
Keywords
UCAV; Tailless; Wind Tunnel Testing; Pitching Moment; Pitch Break; Sideslip Angle;
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Times Cited By KSCI : 2  (Citation Analysis)
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