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 robustness of the scramjet propulsion system,the boundary layer approaching the hypersonic inlet should be turbulent.To develop boundary layer strips for the hypersonic vehicle,a new promising strip configuration with low drag and high efficiency was designed based on the theory of two dimensional hypersonic boundary layer transition and was tested in FD-07 wind tunnel.Whether the inlet is started or not can reflect the boundary layer/shock interaction.The pressure distribution of inlet symmetry planes and shock schlieren will be distinctively deferent for laminar and turbulent on the effect of incident shock,so pressure distri-bution of inlet symmetrical and shock schlieren were used to identify the inlet starting or not and the situation of boundary layer transition can be judged by inlet starting.The tests were conduc-ted including natural transition and artificial transition.The test results show that the boundary layer can be transited successfully using the same strip under the condition of Ma= 5 and 6 ,α=0°,and thus verifies the applicability of the strip which is designed based on the Linear Steady Theory in a wide range of Mach numbers.
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