Recent interest in unmanned combat air vehicles (UCAVs) has motivated investigation of flow structure on delta wings having low and moderate values of sweep angle. This interest leads us to investigate the control of near-surface flow topology of delta wings having a low sweep angle with steady trailing-edge blowing and the effect of angle of attack of planform and different blowing locations on flow structure. Related investigations that were previously done include experimental and numerical studies of the flow structure above wings of low- and moderate-sweep angle and investigations of blowing concept and its effects on flow structures of delta wings. The near-surface flow structure and topology are characterized on a delta wing of low sweep angle, which is subjected to trailing-edge blowing. A technique of high-image-density particle image velocimetry is employed to determine the topological critical points adjacent to the surface and in the near wake of the wing, in relation to the dimensionless magnitude of the blowing coefficient. These topological features are, in turn, interpreted in conjunction with patterns of surface-normal vorticity and near-surface velocity fluctuations, which provide an indication of buffet loading. Even though the jet blowing is at the trailing edge, it has a remarkable, global influence on the surface patterns located well upstream; at high angle of attack, it leads to eradication of large-scale, three-dimensional separation in the vicinity of the apex.
Control of flow structure on delta wing with steady trailing-edge blowing
Strömungsstruktur an einem Deltaflügel mit stationärem Strahlausfluss an der Hinterkante
AIAA Journal (online) ; 44 , 3 ; 493-501
2006
9 Seiten, 11 Bilder, 28 Quellen
Article (Journal)
English
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