A Comparative Correction Method for CFD Numerical Simulation and Wind Tunnel Experiment of Flying Wing Aircraft with Small Aspect Ratio

The state and size of the numerical simulation model and the wind tunnel experiment model are different, which makes the aerodynamic data of the aircraft different. In this paper, two sets of longitudinal aerodynamic data are obtained through CFD numerical simulation and wind tunnel experiment for flying wing aircraft with small aspect ratio, the difference between simulation and experiment is analyzed, the comparative correction method of longitudinal aerodynamic coefficient of flying wing aircraft is established, the correction values of lift coefficient and pitching moment coefficient is obtained, and the difference between numerical simulation and wind tunnel experiment data is corrected. The results show that the corrected aerodynamic data of numerical simulation are in good agreement with the wind tunnel experiment, and meet the accuracy requirements of engineering application.