THE EXPERIMENT INVESTIGATION OF THE EFFECT OF PROPELLER SLIPSTREAM BASED ON WING-TIP SUPPORT AND INDEPENDENT PROPELLER SUPPORT

The propeller slipstream has a very important effect on lift coefficients, drag coefficients, and the pitching moment. The effect of propeller slipstream on aerodynamic characteristics is investigated through an experiment method. Differing from the conventional experiment method for a whole airplane with power, the investigation is launched with a combination of a wingtip supporting measuring system in the three dimensional test section of a NF-3 low-speed wind tunnel of Northwestern Polytechnical University and an independent Propeller-Nacelle supporting measuring system. The effect of the propeller slipstream with a propeller blade angle, the advance ratio and thrust coefficient is mainly investigated. This investigation shows that the lift coefficient of an airplane increases with the increase of the propeller thrust coefficient, and both the drag coefficient and the pitching moment decrease with the increase of the thrust coefficient.