摘要
研究了势流理论下的全机增升装置复杂外形气动力数值计算方法,该方法以低阶面元法为基础,具有计算量小、速度快的优点。复杂流动的粘性效应主要通过附面层粘性修正技术加以体现。采用该方法对某增升装置翼身组合体外形压力分布特性进行计算,并和风洞实验数据相比较,验证了方法的正确性和实用性。在此基础上对某型飞机真实复杂外形的压力分布特性进行了计算,为复杂外形飞行器增升装置的初步设计、方案选型与评估提供了非常理想的工程技术手段。
This paper presents a potential-based flow analysis tool for complex high-lift aircraft configuration. It has the advantage of computing speed, and takes the viscidity effect into consideration by boundary layer correction. First, we use it for a high-lift wing-body and compare the computational results with the experiment data. The good agreement indicates that the method is practicable. Then, a high-lift configuration for a realistic complete aircraft is analyzed. The computing practice shows that the method is a useful means for preliminary design and project evaluating.
出处
《飞行力学》
CSCD
北大核心
2008年第6期26-28,33,共4页
Flight Dynamics
基金
国家自然科学基金资助项目(10772148)
关键词
全机复杂外形
增升装置
面元法
附面层修正
尾迹
飞机
飞行器
complete aircraft configuration
high-lift device
panel method
boundary layer correction
wake
