Aerodynamic Optimization of a Flying V Aircraft Based on the Reynolds-Averaged Navier-Stokes Equations

High-fidelity aerodynamic optimization based on the Reynolds-averaged Navier-Stokes equations is used to investigate the aerodynamic performance of the Flying V aircraft configuration. The Flying V aircraft’s performance is assessed in the wide-body and single-aisle classes, sized to match the capabilities of the Airbus A350-900 and A320neo, respectively. The initial aircraft geometry is chosen to match the planform in Faggiano, F., Vos, R., Baan, M., and Dijk, R., AIAA Paper 2017-3589, and a cabin constraint models the required number of passengers, cargo pallets, and overall shape. Lift-constrained drag minimization is performed with freedom in section shape and twist, while the planform is also allowed to vary, particularly at the single-aisle size. Optimizations are also performed at various center-of-gravity positions to evaluate performance sensitivity to static margin at the wide-body size, while sensitivity to cruise altitude is investigated for the single-aisle Flying V aircraft. At a static margin of 6%, exclusive of nacelles, pylons, and excrescences, the optimized fixed-planform wide-body Flying V aircraft produces a cruise lift-to-drag ratio of about 25.5, while planform optimization enables a cruise lift-to-drag ratio of 27, both at an altitude of 13,000 m. The optimized single-aisle Flying V aircraft produces a cruise lift-to-drag ratio of 23.2 at an altitude of 13,711 m.