Piovesan, TommasoZachos, Pavlos KMacManus, David GSheaf, Christopher2025-01-212025-01-212024-12-31Piovesan T, Zachos PK, MacManus DG, Sheaf C. (2024) Unsteady swirl distortion in a short intake under crosswind conditions. AIAA Journal, Available online 13 December 20240001-1452https://doi.org/10.2514/1.j064226https://dspace.lib.cranfield.ac.uk/handle/1826/23408Under crosswind operating conditions, the flow field of an aero-engine intake can be characterized by notable unsteady flow distortion. These distortions are typically associated with flow separation within the intake as well as with the ingestion of the ground vortex. This unsteady flow distortion can have a detrimental effect on the intake performance and potentially on the operability of the downstream compression system. Measurements of the unsteady velocity field within a model-scale intake under crosswind conditions were acquired using stereo particle image velocimetry (S-PIV). This work analyzes the S-PIV data to quantify the unsteady flow distortion, as well as the characteristics of the ingested ground vortex, in a short intake under crosswind conditions. The swirl distortion metrics were calculated for a range of crosswind velocities and intake mass flow capture ratios (MFCRs). The conditions at which the intake flow separates depend on crosswind velocity, ground clearance, the design of the intake, and the MFCR. Flow characteristics of both low MFCR diffusion-driven and high MFCR shock-induced separation were identified. The circumferential extent and intensity of the swirl distortion are strongly dependent on the crosswind velocity and mass flow rate. The swirl distortion caused by the diffusion-driven separation is greater than that due to the shock-induced separation. The diffusion-driven separation affects a larger portion of the intake aerodynamic interface plane with greater time-averaged and peak distortion levels compared to shock-induced separation. The ground vortex characterization at the aerodynamic interface plane showed a decreasing level of unsteadiness in vortex meandering with increasing MFCR.pp.enAttribution 4.0 Internationalhttp://creativecommons.org/licenses/by/4.0/Vortex DynamicsMass Flow RateParticle Image VelocimetryBoundary LayersFlow ConditionsAircraft EnginesFluid Flow PropertiesCompression SystemsAerodynamic CharacteristicsGerman Dutch Wind Tunnels4012 Fluid Mechanics and Thermal Engineering40 EngineeringAerospace & Aeronautics4001 Aerospace engineering4012 Fluid mechanics and thermal engineeringArticle1533-385X561023