Experimental and Numerical Study on the Vortical Flow of MULDICON Wing Configuration

This paper highlights the results and comparison of flow topology investigation above unmanned combat aerial vehicle (UCAV) configuration, namely, multidisciplinary design configuration (MULDICON), with modified leading-edge profile at apex region from a sharp to blunt reduce complexity structure wing. It was found visualization that low angle attack, for instance, 10°, onset separation took place near region; tip vortex wing also detected. At medium 15°, moved further upstream formation vortex, magnitude increased due increasing incoming attack. higher 20°, intensity vortices shedding is observed. Furthermore, an attack 25°, partially stalled, while complete stalled occurred 30°. The current obtained this study have shown has maximum lift coefficient 0.8 K-Omega-SST turbulence model it 0.93 calculated Spalart-Allmaras model, drag 0.31 0.35, respectively, when AOA 25°. revealed there single leading edge blunt, thus reduced.