In order to support the design of an unmanned gyroplane， a rotor aerodynamics model based on blade element theory and dynamic inflow is developed to perform rotor parameter analysis. The influence of rotor radius and collective pitch on rotor thrust and shaft angle is discussed， and the law of rotor thrust and control is obtained. The experiments of unmanned gyroplane are conducted in the low speed wind tunnel， including the single fuselage experiment and the fuselage and rotor group experiment. The rotor lift and drag at different wind speeds and angle conditions are measured. The validity of the computing method is verified by comparing the experimental results with the computed result. By computational analysis and experimental study， rotor aerodynamic characteristics versus design parameters， flight state， and shaft angle are investigated. In the end， the formula for rotor thrust on flight speed and shaft angle is observed.