Propeller Performance at Large Angle of Attack Applicable to Compound Helicopters

An experimental dataset is presented of propeller performance in static condition and at low subsonic airspeeds for various angles attack up to 90 deg. Numerical investigation through a Reynolds-averaged Navier–Stokes computational fluid dynamics model revealed the mechanisms behind changes with advance ratio, angle attack, configuration changes. The was found be free major errors very suitable validation models. Furthermore, aerodynamic interaction an upstream wing tested normal flow, represent occurring time-averaged main rotor slipstream on compound helicopter. From numerical it concluded that results are qualitatively representative this interaction. data showed addition net reduction all quantities, thrust reducing 20%. Thrust decreasing increasing were numerically. For most operating conditions, resulted small decrease thrust-over-power ratio. Decreasing distance, flap deflection generally decreased effect power; however, influence small.