翼身融合布局是未来民机最有可能实现的非常规布局形式，其气动布局方案的验证通常采用缩比模型飞行试验的方式进行。以某翼身融合布局低速验证机为研究对象，以数值计算方法为基础，分析了其在飞行试验中存在的纵向和横向不稳定现象，提出了改善的方案——增加前缘缝翼。对此验证机进行前缘缝翼的气动布局设计、典型翼型的二维前缘缝翼设计和机翼三维前缘缝翼的气动设计，利用数值计算方法对设计结果进行纵向和横向分析。结果显示，所设计的前缘缝翼可以明显地增大验证机的失速迎角，改善其纵向力矩特性和横向特性。
Blended-wing-body configuration could be the most promising irregular configuration in the future. The verification of its aerodynamic layout is usually carried out through a scaled model flight test. Using the numerical method, this paper analyzes the instability in both transverse and longitudinal directions during the verification flying test and proposes an improvement plan of adding slat. We designed the aerodynamic layout of the slat for the testing aircraft, and 2D and 3D slat for the typical wing-shape. Results are analyzed on both the transverse and the longitudinal directions through numerical simulation, indicating that the designed slat can significantly enlarge the stall angle of attack and improve the moment characteristics on transverse and longitudinal directions.
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