Transactions of Nanjing University of Aeronautics & Astronautics
Investigation on Aerodynamic Interaction of Tandem Tilt-Wing and Multi-rotor in Transition Condition
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Abstract:
The complex aerodynamic interaction between tandem tilt-wing and multi-rotor directly affects the wing surface flow and rotor thrust， making it a critical factor during the tilt transition process of this configuration of rotorcraft. The aerodynamic interaction of tandem tilt-wing and multi-rotor is investigated based on the CFD method. The aerodynamic effect of multi tilt-rotor is simulated as virtual disk modeling by adding source terms to the Navier-Stokes equations， effectively reducing the calculation time while maintaining the accuracy of aerodynamic interaction calculations. Aerodynamic forces and flow field characteristics of the tandem tilt-wing and multi-rotor under different tilt angles are compared between cases with and without aerodynamic interaction. Furthermore， the differences in aerodynamic forces between dynamic tilt transition and fixed-angle conditions were compared. The results show that the aerodynamic interaction of multi-rotor obviously increases the lift of front tilt-wing at different tilt angles， the wing lift under interaction is increased by more than 40% compared with isolated wing at tilt angle of 15°for the computation in this paper， which is related to the increase of wing flow velocity and the suppression of flow separation caused by multi-rotor； the wing blocking effect will increase rotor thrust， especially near the tilt angles of 30° and 45°； the increases of rear wing lift and rear rotor thrust under aerodynamic interaction are not significant because of suppression by the front wing’s downwash； the unsteady effects during dynamic tilting have a relatively minor impact on aerodynamic interaction， with the aerodynamic forces on the rotors and wings during the dynamic tilting process showing little difference from those under corresponding fixed tilt angles.
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Project Supported:
This work was supported by the National Key Laboratory of Helicopter Aeromechanics Fund（No.2024-CXPT-GF-JJ-093-05）.
Clc Number:
V211.52
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