Evaluation of Acrobatic Aircraft Performance: Multidisciplinary Wing Optimization with DOE and RSM Techniques

This research employs a performance-oriented approach to determine an acrobatic aircraft's optimal wing size and configuration. To establish wing geometry, a design of experiments methodology is utilized to generate design points for key variables to optimize the wing design. These design point data are then used to create a response surface model. The analysis of the response surface reveals the interconnections between design parameters and the lift and drag coefficients of the aircraft. The findings suggest that an increase in velocity enhances the lift and drag coefficients, whereas an increase in aspect ratio reduces the aerodynamic efficiency due to the parasite drag increase. Both the twist angle and the taper ratio positively impact the lift coefficient increment, drag coefficient reduction, and stall angle of attack (AoA) increase. However, the wing sweep angle does not affect lift and drag coefficient change in this plane category. The optimization of geometric parameters is achieved through a multi-objective genetic algorithm. The optimized wing exhibits an improved suction surface pressure distribution, improving the aerodynamic performance and stall AoA. The aerodynamic efficiency plot reveals a ۴% improvement in the lift curve slope, indicating enhanced AoA performance. The optimized pressure distribution and aerodynamic performance contribute to a ۳.۴۳% increase in aircraft roll rate.

کلیدواژه ها:

Aerodynamic Performance ، Computational Fluid Dynamic ، Design of Experiment ، Multidisciplinary Optimization ، Response Surface Methodology ، Wing Design