Application of boundary conditions “actuator disk” in computational study of aerodynamic interference of the engine and airframe of a passenger aircraft
Computational methods for obtaining aerodynamic characteristics of an aircraft are currently a source which supplements the data of aerodynamic experiment. This applies to the improvement of local aerodynamics, as well as the impact of the power plant on the flow around the airframe and aerodynamic characteristics of the aircraft. Despite the development of computational methods and computer technology, the tasks of integrating the power plant impose requirements for the refinement of the computational model, which are not fully implementable within the design cycle. However, simpler models can be potentially improved for situations of moderate aerodynamic interference by taking into account the profiles of variables in the air intake formed when the fan is in the nacelle. The paper considers the application of variants of the boundary condition “actuator disk” in the computational study of the contribution of the working power plant to the aerodynamic characteristics of the configuration. The approach is reliable for solving problems of weak and moderate aerodynamic interference. Engine performance has a weak effect on the overall aerodynamic characteristics at small angles of attack, but the component contributions caused by this factor are noticeable and have a different sign, which indicates the need to analyze this interaction.
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