This paper presents aerodynamic analyses of a transonic transport aircraft wing equipped with hybrid laminar flow control and variable camber systems. The analyses are performed on multiple fidelity levels, where particular focus within this paper lies on the efficient introduction of the high-fidelity (HiFi) computational fluid dynamics (CFD) results into the aerodynamic module of the overall aircraft design suite MICADO, representing the low-fidelity (LowFi) level. The introduction on integral coefficient level is achieved via the formulation of a Gaussian process regression-based surrogate model (SG) for the drag coefficient of the wing. Surface pressure distributions are predicted with a reduced-order model (ROM) utilizing Proper Orthogonal Decomposition. The predictions of both models are in good agreement with HiFi CFD results. Integrating the SG/ROM into the LowFi-environment reveals that both LowFi and HiFi approaches correspond well in predicting parametric sensitivities. Nevertheless, the SG/ROM integration substantially improves aerodynamic prediction accuracy at moderate computational and modeling costs.      «

This paper presents aerodynamic analyses of a transonic transport aircraft wing equipped with hybrid laminar flow control and variable camber systems. The analyses are performed on multiple fidelity levels, where particular focus within this paper lies on the efficient introduction of the high-fidelity (HiFi) computational fluid dynamics (CFD) results into the aerodynamic module of the overall aircraft design suite MICADO, representing the low-fidelity (LowFi) level. The introduction on integral...     »