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A. Hövelmann, S. Pfnür, C. Breitsamter
The efficiency of deflected midboard flaps is investigated on a diamond wing shape unmanned aerial vehicle, the SAGITTA demonstrator configuration. The Reynolds-Averaged Navier-Stokes equations are applied to compute numerical results for a variety of flight conditions with varying angle of attack, sideslip angle and midboard flap deflection. Low speed wind tunnel conditions are regarded in order to compare the results to existing experimental data. The focus is particularly laid on the analysis of the aerodynamic coefficients and derivatives in both the longitudinal and the lateral motion. Occurring flow phenomena are motivated and discussed by flow field illustrations that are available from the numerical computations. At small to moderate angles of attack, the overall flow field is dominated by attached flow, which is associated with linear flap characteristics. With increasing angle of attack and additional sideslip angle, the leading-edge vortex originating from the inboard sharp leading-edge and the wing tip separation region affect the midboard flap efficiency in some extent. The roll control effectiveness is mostly ensured, but non-linear coupling effects become obvious, which are analyzed and discussed.
Deutscher Luft- und Raumfahrtkongress 2014, Augsburg
Verlag, Ort:
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2014
Conference Paper
21,0 x 29,7 cm, 15 Seiten
Stichworte zum Inhalt:
cfd analysis, wind tunnel testing
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