Aerodynamic optimisation of civil aero-engine nacelles by dimensionality reduction and multi-fidelity techniques

Purpose Aerodynamic shape optimisation is complex because of the high dimensionality problem, associated non-linearity and its large computational cost. These three aspects have an impact on overall time design process. To overcome these challenges, this paper aims to develop a method for transonic aerodynamic with reduction multifidelity techniques. Design/methodology/approach The developed methodology used installed civil ultra-high bypass ratio aero-engine nacelle. As such, effects airframe-engine integration are considered during routine. active subspace applied reduce problem from 32 2 variables database compiled Euler fluid dynamics (CFD) calculations. In reduced dimensional space, co-Kriging model built combine lower-fidelity Reynolds-averaged Navier stokes higher-fidelity CFD evaluations. Findings Relative baseline nacelle derived isolated process, proposed yielded non-axisymmetric configuration increment in net vehicle force 0.65% nominal standard thrust. Originality/value This work investigates viability through combination demonstrates that enables problems.