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Analysis of the Impact of Aircraft Manoeuvring on Intake Disturbance


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DOI: https://doi.org/10.15866/irease.v16i4.23749

Abstract


The article presents the issue of stable operation of the intake system, which is particularly important for the case of high-maneuverability combat aircraft, where high values of critical angles of attack and bank angles can lead to the formation of disturbances in the intake area. This problem is related to the issue of optimization of any intake system, through the stability of engine operation, where the most important in the operation of the intake system is the homogeneity of the pressure field in the output section, in front of the engine fan (AIP). In this paper, the parameters CDI, RDI, MPR and DPC have been used to evaluate the pressure field disturbance. A built model of the intake system with a 3D fuselage has been used to study numerically the impact of the maneuvers performed by the aircraft. The conditions for analyzing the operation of the intake system have been established in accordance with the Aircraft Flight Manual (AFM). Numerical calculations have been performed for six cases of angles of attack. The calculations have provided information on pressure distributions, problems of flow separation at the edge of the inlet and the behaviour of the boundary layer. Characteristics have been developed by showing the changes in the contributions of each pressure group. The determined coefficients give a complete characterization of the disturbance in the intake system for the given conditions associated with the assumed flight parameters.
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Keywords


Mechanical Engineering; Turbine Aircraft Engines; Surge; Compressors; Intake Systems

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References


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