Nacelle intake flow separation reduction at cruise condition using active flow control

Turbofan engine intakes are designed to provide separation-free flow at the fan face over a wide range of operating conditions. But some off-design conditions, like high flight speeds and angles attack (AoA), aero intake may encounter separation. This boundary layer separation inside nacelle inlet an aircraft can lead large number undesirable outcomes reduction in efficiency, stall levels stress on blades. Active control is promising solution reduce associated fan-face distortion such By blowing pressurized air into near point, energized be controlled. study investigates applicability lip blowing, active technique, fan-face. First, was triggered 3D CFD model based NASA Common Research Model (CRM) using AoA cases cruise condition (Mach 0.85, Mass capture ratio ∼0.7) features separated were analyzed. Thereafter, introduce form two types direct pitched blowing. The efficacy achieving ultra bypass turbofan has been established through this study. present paper also examines significance parameters type pressure ratio, slot dimension, different identify critical parameters. Our research successfully establishes proof concept by demonstrating feasibility for aero-intakes, via numerical modelling. Furthermore, provides crucial insights regarding important variables considered future experimental studies, detailed studies covering wider