An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless Aircraft

This paper puts forward an aerodynamic design method to improve the high-speed performance of aircraft with low-aspect-ratio tailless configuration. The can ameliorate longitudinal moment characteristics configuration by designing and collocating key section airfoils constrains fixed parameters planform shape capacity. Firstly, effect twisting wing, fore-loading aft-reflexing on is evaluated high-fidelity numerical methods, quantified defining trimming efficiency factors. Then, a linear superposition formula obtained analyzing rule factor, based collocation methods are achieved. According trimmed obtained. results computational fluid dynamics (CFD) wind tunnel tests show that has smaller zero-lift pitching higher available lift-to-drag ratio than initial at cruise, besides achieves principle raised for configuration, which be described as zero-pitching moment, cruising lift coefficient, maximum coincident. In addition, off-design conditions, shows favorable drag divergence characteristics, satisfactory medium-altitude maneuvering condition, good stall pitching-moment low speed state.