This thesis addresses transonic aerodynamic drag reduction within a shape optimization loop. The wing is treated as a sub-model of an aircraft-level optimization process, in a hybrid wing body (HWB) context. The problem consists of minimizing drag at a prescribed lift, while the pitching moment is monitored through a constraint.
The numerical chain couples computer-aided design (CATIA V5), mesh generation (Pointwise), CFD simulation based on the Reynolds Averaged Navier-Stokes (RANS) equations (SST k-ω turbulence model, ANSYS Fluent) and post-processing (ParaView), driven by the NSGA-II genetic algorithm within modeFRONTIER. The method is first applied to the transonic RAE2822 airfoil using two parameterizations (NURBS and iCST), then extended to a three-dimensional wing through section camber and twist adjustment.
The results show a notable drag reduction at constant lift, on the order of 20 to 30% depending on the case, achieved mainly through weakening of the upper-surface shock and a redistribution of the spanwise load. The pitching moment remains controlled and its magnitude decreases slightly, which reduces the trim effort at the aircraft level. These results provide a methodological basis for optimizing the wing as a sub-model of a full-aircraft optimization loop.
| Date | 24 Aug 2026 |
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| Original language | French |
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| Awarding Institution | - École de technologie supérieure
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| Supervisor | Patrick Germain (Supervisor) |
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Fezeu Kembe, D. (Author),
Germain (Supervisor),
24 Aug 2026Student thesis: Master's thesis › Master in Engineering: Engineering