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The flowfield generated by a helicopter in flight is extemely complex, and it has been recognized that interactions among components can significantly affect helicopter performance. In the present work a simplified model for the interaction of a rotor tip vortex with the helicopter fuselage is developed. The tip vortex is idealized as a single three-dimensional vortex tube, and the fuselage is moleded as an infinite circular cylinder
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Affes et al. (1993) studied this question.
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