Effects of canard–wing interference on the ﬂight characteristics of a civilian transonic cruiser aircraft are examined using computational ﬂuid dynamics (CFD) simulations, a vortex lattice solver, and wind tunnel measurements. These data sources are used to generate reduced-order aerodynamic models in the form of look-up tables that give longitudinal and lateral force and moment coeﬃcients for different combinations of angle of attack, Mach number, side-slip angle, and canard deﬂection angle. Flight characteristics from CFD simulations and the vortex lattice solver are compared with wind tunnel measurements in order to determine model accuracy for both static and dynamic ﬂight conditions. Static cases are examined at a Mach number of 0.1 for two different canard positions using an overset grid approach. Cases considered include canard deﬂections of −30◦, −10◦, 0◦, and 10◦ at angles of attack ranging from −4◦ to 30◦ and for sideslip angles of −6◦ and 6◦. Dynamic cases are examined for aircraft oscillations about mean angles of attack of 0◦ to 10◦, with a motion frequency of 1 Hz and an amplitude of 0.5◦. The results indicate that both static and dynamic aerodynamic predictions from CFD simulations are in good agreement with experiments over the range of conditions considered. The vortex lattice solver, by contrast, cannot predict vortical ﬂows formed over the wing and canard surfaces, resulting in poorer agreement with experimental data. The CFD-based reduced order aerodynamic model is then used to investigate trim settings and handling qualities of two different canard designs. Results show that positioning the canard surface of the transonic cruiser closer to the wing requires less canard deﬂection and thrust force to trim the aircraft.