Several static and dynamic forced-motion wind-tunnel tests on a generic unmanned combat air vehicle configuration with a 53 deg swept leading edge are reviewed. The static tests include both subsonic and transonic measurements. These tests are part of an international research effort to assess and advance the state-of-the-art of computational-fluid-dynamics methods to predict the static and dynamic stability and control characteristics for this type of configuration. The tests included analysis of trailing-edge control surface effectiveness. This paper describes the data collected from three different models of this unmanned combat air vehicle configuration in four different wind tunnels. A subset of this large experimental dataset was selected as focus test cases for computational-fluid-dynamics comparison. The focus test case data are presented in detail.
Experimental Investigations of a Generic Swept Unmanned Combat Air Vehicle with Controls
Journal of Aircraft ; 55 , 2 ; 475-501
2016-07-25
27 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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