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... »