PROPELLER-INDUCED EFFECTS ON THE AERODYNAMICS OF A SMALL UNMANNED AERIAL VEHICLE doi: 10.5028/jatm.2012.04043112

PROPELLER-INDUCED EFFECTS ON THE AERODYNAMICS OF A SMALL UNMANNED AERIAL VEHICLE doi: 10.5028/jatm.2012.04043112

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The present paper has discussed investigations about the propeller slipstream effects on the aerodynamics of a generic unmanned air vehicle platform in the wind tunnel for a broad advance ratio range.The propeller-induced effects for turbo air m3f24-1 small unmanned air vehicles are more significantly pronounced than general aviation aircraft, because of their high propeller-diameter-to-wing-span-ratio.The stall angle of attack of the small unmanned air vehicle is generally delayed under slipstream effects.

The study evaluated the shift in stall angle of attack as a function of propeller-diameter-to-wing-span and advance ratios of the propeller.The aerodynamics of the unmanned air vehicle platform is estimated through wind-tunnel experiments.The study reported in this paper is part of an effort to develop the framework for the analysis of propeller-wing interaction for small/micro unmanned air vehicles at an early design discount greenery stage.

Specifically, the slipstream effects on the aerodynamics of a generic small unmanned air vehicle are studied in the wind tunnel for the shift in the aircraft stall angle of attack.The lift-curve slope of the aircraft is independent from the variation of advance ratio.The stall characteristics show strong dependence on the advance ratio.

Therefore, the relationship is modeled accurately using inverse-quadratic relationship.This empirical trend of the stall behavior with advance ratio can be useful in the analysis and simulation of the resulting flight and estimation of performance envelopes.