摘要
为改善升力体的低速气动性能 ,探讨各种措施对升力体低速气动特性的影响 ,在风洞中对一个碟形低速升力体半模型进行了实验研究 .试验结果表明 ,采用适当的气动设计与附面层控制相结合 ,可以明显改善升力体的低速气动性能 ,其最大升阻比达到 1 8.7,与原来相比提高了 86% ,而且零升阻力降低 5 6% ,大迎角气动特性也有一定的改善 .实验中还对 2种附面层控制方案进行了对比 ,给出了相应的试验结果 ,对其控制机理进行了初步的探讨 .实验证明该碟形低速升力体气动性能优秀 ,并且已经成功进行了模型空中试飞 .
Wind tunnel experiments of a saucer-like low speed lifting-body were conducted, for the purpose of improving its low speed aerodynamic performance and investigating effects of various aerodynamic factors. Aerodynamic coefficients were measured in the wind tunnel experiments, some different methods of boundary- layer control were compared and their characters were described. These results showed that combined with proper aerodynamic design and boundary layer control, the performance of the saucer-like low speed lifting-body can be improved significantly. The highest lift to drag ratio is up to 18.7, 86% improvement relative to its prototype, with the zero-lift drag coefficient being decreased 56%. With boundary layer control instruments, aerodynamic performance at high angle of attack is also improved. Experiments approved that this saucer-like lifting-body takes the advantage of less outer size and higher carrying capacity, and lest flight of its ratio control flight model has been accomplished successfully.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2003年第4期346-349,共4页
Journal of Beijing University of Aeronautics and Astronautics
关键词
升力体
升阻比
附面层控制
Aerodynamics
Boundary layers
Wind tunnels
