Regionalized Actuator Disk Model Designed by Optimization Method for Propeller Slipstream Computation

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Abstract
In this paper a new actuator disk model is designed with regionally distributed parameters varying along both radial and circumferential directions to improve the simulation of classical actuator disk model which loses flow reality downstream in the case of high angle of attack. Parameters of pressure jump and tangential velocity in different regions are obtained according to the idea of best fitting with optimization method. Comparisons of flow field data between regionalized actuator disk model and full blade model show that the new model offers a better agreement than classical model in the case of high angle of attack. Results of this study confirm that the regionalized actuator disk model can benefit full aircraft computation.