Aerodynamic Configuration Design Of Flying Wing Transport

Flying wing seems to be one of the most promising concepts regarding very high capacity aircrafts. So, such configuration has been the subject of aerodynamic design of interest recently. Since the development of aerodynamics and flight control, the stability and maneuverability problems of flying wing configuration could be solved. Therefore, such configuration achieves a clean aerodynamic and efficient structural design that offers tremendous potential for increased aerodynamic efficiency and stealth performance, and reduced fuel burn, weight, and cost. In this thesis, based on analysis of abundant research achievement, the flying wing configuration is applied to civil transport of large capacity. At the cruise condition, a high subsonic flying wing configuration for transport of 200 ton take-of weight is designed for the first time.The main research issues and achievements in this thesis are as follows:1. According to the advanced research achievement of flying wing configuration, combined the performance target of actual popular transports, the design objective of 200 ton take-of weight and 50 ton payload for high subsonic flying wing transport is brought forward.2. Using modern aircraft design theory and method, integrated the characteristic of flying wing configuration, the weight, wing load and etc of the flying wing transport are evaluated. According to the evaluation result, applying computer 3D modeling technique, the original aerodynamic configuration is built.3. By Computational Fluid Dynamics technology, the Euler equations numerical algorithm with boundary layer viscosity modification is applied to evaluating the aerodynamic performance of original flying wing configuration. According to the evaluation result, the insufficiency and the reason of aerodynamic performance for original configuration is analyzed.4. For solving the problem of original configuration, researching the effect of different combination of aerodynamic parameters and geometry parameters on aerodynamic performance, the feasible design method is put forward. By aerodynamic evaluating, the improved configuration which could meet the design requirement is achieved.5. Analyzing the aerodynamic evaluation result obtained during the design procedure, the phenomena and design law of aerodynamic configuration design for flying wing transport are obtained.