Abstract

Results we presented which illustrate the mutual interactional aerodynamic effects between a small-scale articulated rotor and a fuselage consisting of a body of revolution. Wind tunnel tests were conducted on the isolated fuselage, the isolated rotor, and the rotor/fuselage combination from hover up to an advance ratio of 0.15. Forces and moments on the fuselage and rotor were measured by independent strain-gauge balances. Both steady and unsteady pressure measurements on the fuselage. The results have shown that large downloads and pitching moments are created on fuselage due to the presence of rotor wake. These loads were significantly affected by variations in both rotor thrust and advance ratio. The results have also shown that the presence of the fuselage produces an increase in rotor thrust over and above the isolated rotor performance. The aerodynamic characteristics of both the fuselage and the rotor were found to approach their isolated component values as the advance ratio was increased. Unsteady pressure fluctuations on the fuselage were extremely significant and often exceeded the mean pressure values. These unsteady pressures were present over the full range of test conditions, even at high advance ratios where the wake is highly skewed behind the rotor. These unsteady pressure loads are shown to be due to the periodic passage of the rotor blades coupled with the impingement of the rotor wake vortices on the fuselage. Nomenclature b Number of blades c Blade chord, m C~~ Fuselage lift coefficient in wind-axis, Lrl(qmSr) c~~ Fuselage moment coefficient in wind-axis, Mf I(qwSf 4 CP Time averaged pressure coefficient,

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