Modern tactical aircraft designs and future civil transportation concepts often feature highly contoured engine intake geometries. This leads to complex aerodynamic phenomena within the intakes which can cause substantial distortions of the ow delivered to the compressor. This paper presents a CFD-study of the in uence of varying in ow conditions represented by di erent Mach and Reynolds numbers at the duct inlet onto the ow  eld in a generic s-shaped intake geometry. The CFD-setup is  rst validated against experimental data provided by Wellborn et al.1 and the suitability of di erent turbulence models has been investigated. Based on the validated setup, a script-based procedure has been developed to perform RANS- simulations of the ow inside the generic s-duct with di erent inlet conditions fully automated with the commercial CFD-code ANSYS CFX. The inlet conditions have been varied according to di erent aircraft operation points within the range of a generic ight envelope typical for subsonic aircraft operation. The number of the conducted simulations allows not only an overall prospective view how total pressure or swirl distortion parameters change within the envelope under consideration here. It furthermore gives the opportunity to dedicately investigate the decoupled e ects of varying Mach and Reynolds numbers on the aerodynamics within the duct and the developing distortions. Thereby both the distortion intensity as well as their spatial characteristics are considered by using di erent distortion description parameters.    «

Modern tactical aircraft designs and future civil transportation concepts often feature highly contoured engine intake geometries. This leads to complex aerodynamic phenomena within the intakes which can cause substantial distortions of the ow delivered to the compressor. This paper presents a CFD-study of the in uence of varying in ow conditions represented by di erent Mach and Reynolds numbers at the duct inlet onto the ow  eld in a generic s-shaped intake geometry. The CFD...    »