Experimental Investigation of Performance of the Rotorcraft Directional Rudder

Abstract

The paper presents the results of gyrocopter fuselage experiment testing in a wind tunnel. The model subjected to testing was made in 1:8 scale by 3D printing. The tests included the measurement of forces and aerodynamic moments acting on the model, for a variable fuselage sideslip angle (-20º to 20º), and for three different positions of the rudder setting (0º, +5º, +10º). The measurement was carried out at an airspeed of 25 to 26 m/s. Based on the measured values, aerodynamic drag coefficients, lift coefficient and aerodynamic moment coefficients with respect to all axes of the reference system, were determined. The measurements carried out have facilitated the derivation of diverse characteristics, validating our conclusions. The results and conclusions drawn from these experiments can be valuable in enhancing the design and functionality of rotorcraft rudders.

Keywords

• gyrocopter
• wind tunnel
• aerodynamic research
• directional rudder
• sideslip angle