Aerodynamic and geometric optimization of a transport aircraft wing using design of experiments

Date

2024-4-15

Author

Kavak, Ceyda

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Transport aircraft are used for passenger and cargo transportation where the design should be optimized for an efficient operation. As wings are the major lifting surfaces of an aircraft, the optimization of the wing geometry is crucial for a successful aircraft design. This thesis aims to achieve an optimized wing configuration for a transport aircraft using Design of Experiments (DOE). The design space is constructed by altering 12 design variables that define the wing geometry and the operating angle of attack. The goal of the optimization is to obtain a wing configuration with the minimized drag force and weight, which is capable of generating the required lift that compensates the aircraft weight for a cruise condition of M=0.75. To obtain the aerodynamic coefficients, Computational Fluid Dynamics (CFD) analyses are carried out by solving Reynolds Averaged Navier-Stokes (RANS) equations, where the processes of geometry generation and flow simulation are automatized. In the scope of DOE, screening design and response surface design (RSD) are conducted to identify the most influential design variables on the system responses and achieve the optimized wing configuration by building a surrogate model representing the relationship between the inputs and outputs of the optimization problem.

Subject Keywords

Aircraft wing design, Computational fluid dynamics, Design optimization, Design of experiments

URI

https://hdl.handle.net/11511/109489

Collections

Graduate School of Natural and Applied Sciences, Thesis