Abstract
Abstract : Modern fighter/attack aircraft rely on vortex flow to increase lift at moderate to high angle of attack alpha. Therefore, a great deal of interest exists in understanding and predicting the vortical flow structure generated by swept wings. One form of vortex control uses small geometry modifications ( fillets) at the strake-wing junction to alter the vortex dynamics. Fillets are also possible candidates for roll control devices, being deployed symmetrically for enhanced lift and longitudinal control or asymmetrically for lateral-directional control. Various studies have looked at the effect of fillets on the interaction of the wing and strake vortices. The primary objective of the present experiment was to investigate the lift characteristics of fillets on a three-dimensional model and compare the results to a flat-plate model with the same platform. It was also hoped to experimentally validate and quantify the increase in lift as a result of fillets on flat-plate models with the same planform as the three-dimensional model. A secondary objective was to evaluate the effect of a simple centerbody on the lift of flat-plate models with and without fillets as a means for comparison to the full three-dimensional model.
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