新型高超声速进气道边界层人工转捩方法研究

发布时间：2018-03-10 20:08

本文选题：高超声速进气道　切入点：边界层人工转捩　出处：《实验流体力学》2016年02期 　论文类型：期刊论文

【摘要】：为确保高超声速进气道的安全工作,其压缩面边界层在进入其内流道前必须完成转捩。针对高超声速进气道边界层转捩需要,依据二维高超声速边界层转捩机理,尝试了一种新型低阻高效的边界层人工转捩方法,在FD-07风洞中开展了试验验证。试验中首先通过进气道对称面压力分布和激波纹影获得进气道的自起动情况,进而推断进气道入口前的边界层转捩情况。试验包括进气道前体边界层自然转捩和人工转捩,试验结果表明在Ma=5、6,迎角α=0°来流条件下,使用同一波长的人工转捩带可以成功实现进气道边界层转捩,验证了基于线性稳定性理论设计的人工转捩带在宽马赫数范围的适用性。
[Abstract]:In order to ensure the safe operation of hypersonic inlet, the boundary layer of hypersonic inlet must complete the transition before entering its inner channel. According to the mechanism of two-dimensional hypersonic boundary layer transition, the hypersonic inlet boundary layer transition needs to be met. A new method of artificial boundary layer transition with low resistance and high efficiency was tried and tested in FD-07 wind tunnel. The self-starting of the inlet was obtained by the symmetrical plane pressure distribution of the inlet and the ripple shadow of the inlet. Furthermore, the boundary layer transition before inlet inlet is inferred. The experiment includes natural transition and artificial transition of inlet precursor boundary layer. The experimental results show that under the condition of Maxi 5, 0 掳angle of attack, The artificial transition band of the same wavelength can successfully realize the boundary layer transition of the inlet, which verifies the applicability of the artificial transition band designed based on the linear stability theory in the wide Mach number range.
【作者单位】：中国航天空气动力技术研究院;
【基金】：航天技术自主研发基金
【分类号】：V211.48

【相似文献】