Conceptual Design of Distributed Propeller Aircraft: Linear Aerodynamic Model Verification of Propeller-Wing Interaction

Abstract

This paper opens an exciting new opportunity of new aircraft concepts specifically targeting to have higher aerodynamic efficiency than conventional designs through the synergistic interaction between the propeller and the wing. Previous literature on propeller and wing performance analysis methods provide a platform on theory description behind the aerodynamic modeling approach selected. The research effort began with attempts to verify previous NASA wind-tunnel tests (TN D-4448) on a medium and short wing span propeller-driven, short take off and landing (STOL) transport aircraft. One prediction is employed on isolated performance of the wing without the propellers and another is to capture one-way coupling, specifically the effect of the propeller slipstream on the wing. For the first decoupled analysis configuration , the vortex lattice model (VLM) technical tools comparison was made with the Athena Vortex Lattice (AVL) and VSPAERO. Next, the propeller and the wing interaction is predicted using three different coupling methods. The first stage of the work is based on VSPAERO solver which combined the actuator disk theory with VLM. The second approach is to compare with the in house code of blade element and lifting line theory (LLT) coupling. Thirdly, to couple the same BET model with VLM to capture the aerodynamics performance and the influence of the propeller on the wing with the aim to determine the lift and induced drag of the configuration. Perhaps the most compelling aspect offered by the technical tools selected is being economic; low computational cost and time. The numerical computation results of the model presented a good correlation with the experimental data. The aerodynamic model developed will be a strong base for more complex analysis and even greater efficiency improvements for a conceptual design studies of future distributed propeller aircraft .