Synthesis of the Aerodynamic Model of a Flying Wing Aircraft

Flying-wing aircraft, such as the Flying V considered in this study, can substantially contribute to reducing the carbon footprint of the aviation sector. To enable adequate predictions regarding performance, stability, and control, a validated aerodynamic model of the Flying V is derived in this paper. The first part of the paper compares the aerodynamic coefficients determined with experiments and simulations conducted on a subscale version of the aircraft. The experiments are conducted in a wind tunnel and with flight tests, while the simulations are conducted using a vortex lattice method (VLM), a panel method, and a numerical method based on the Reynolds-averaged Navier–Stokes (RANS) equations. The comparison highlights the dependency of the aerodynamic coefficients on the angle of attack, which influences the flow acting on the aircraft. Based on the results of this comparison study, the full-scale aircraft aerodynamic model is derived by combining RANS and VLM simulations calibrated with experimental data. All aerodynamic coefficients are derived as a function of the angle of attack and at different Mach numbers and altitudes.