平流层飞艇纵向气动特性及减阻实验研究

Experimental investigation on the longitudinal aerodynamic performance and drag reduction of a stratospheric airship

以美国高空哨兵50平流层飞艇作为背景样机,通过风洞实验研究了布局形式对该型飞艇纵向气动特性的影响。研究表明:与Y形尾翼相比,十字尾翼布局形式具有更大的阻力和升力;从俯仰静稳定性的角度而言,十字尾翼在大迎角下使得飞艇从纵向静不定变为纵向静定;但由于尾翼产生较大的附加阻力,因此需要采取一定的减阻措施。进一步采用微型涡流发生器对飞艇的后体及尾翼处的流动分离进行控制,研究其在不同迎角和侧滑角工况下的减阻效能,发现在α=8°、β=0°或β=-8°、α=0°工况下可以获得减阻效果,且MVG布置更密时,获得的减阻效果更好。

A wind tunnel test is performed to investigate the effect of different configurations on the lon-gitudinal aerodynamic performances of a stratospheric airship model based on the prototype of HiSentinel Airship 50.It is found that the cross fin configuration has larger drag and lift than the Y fin configuration. The cross fin configuration also provides larger pitching momentum,which suggests a positive effect for the improvement of the airship static stability.Considering the additional drag component induced by the cross fin,micro vortex generators （MVG）are fixed at the rear end of the airship to inhibit flow separation of aft-body and reduce the total drag.The result shows that,in the case ofα=8＆#176;,β=0＆#176;orβ=-8＆#176;,α=0＆#176;,the adop-tion of MVGs brings a relatively significant drag reduction,and the efficiency still higher for smaller and closer MVGs.