A multi-objective optimization framework for three-dimensional intakes of ultra-high-bypass-ratio engines has been developed. The principle underlying the approach is to conduct the design of experiments simultaneously at low-speed and cruise operating points using computational fluid dynamics. Three low-speed points are considered: high incidence, crosswind, and static start. An over-wing-nacelle configuration was investigated at cruise. An experimental campaign is presented to validate the low-speed numerical setup. The design study was performed on intakes with length-to-fan-diameter ratios () of 0.65, 0.50, and 0.35, respectively. Stable parameter ranges were identified within which the intakes could operate without flow separation. Shortening the intake length improved the stability margins of the intake, especially for the contraction ratio. At cruise, the diffuser cone angle was found to be the most critical parameter influencing the intake pressure recovery. Surrogate models were fit to the data from the design of experiments. A trade-off analysis was performed to identify an optimum trade-off between cruise and low-speed conditions. Final three-dimensional intake candidates were seen to operate without separation at all low-speed conditions. At cruise, the short intake showed a 0.08% improvement in intake pressure recovery and a drag penalty of 87.05 drag counts compared to the long intake.
Multipoint Aerodynamic Optimization of Three-Dimensional Ultra-High-Bypass-Ratio Engine Intakes
Journal of Propulsion and Power ; 41 , 3 ; 365-380
2025-05-01
Conference paper , Article (Journal)
Electronic Resource
English