| 摘要: |
| 基于下颌式进气道将Bump/前体一体化设计方法应用于进气道设计，采用特征线法设计五种不同型面的前体，并采用数值仿真的方法，计算每种Bump/前体一体化进气道的自起动过程。研究表明:加入合适的Bump型面可极大提高进气道起动性能，将横向压力梯度集中在侧板附近的构型使进气道自起动马赫数降低了0.95。Bump/前体一体化对不起动状态下分离区形态进行三维重构，改变了分离区内横向溢流，从而改变了进气道起动能力。另外，通过对进气道起动过程的研究发现，进气道内形成封闭式分离区时，通常在高于设计马赫数时才能起动，进气道设计中应尽量避免这种状态的出现。 |
| 关键词: 进气道 Bump 起动 分离区 |
| DOI： |
| 分类号: |
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| 关键词:进气道；Bump；起动；分离区 |
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XU Shang-cheng,WANG Yi,WANG Zhen-guo,FAN Xiao-qiang
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(Science and Technology on Scramjet Laboratory，National University of Defense Technology，Changsha 410073，China)
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| Abstract: |
| The method of Bump/forebody integration is employed in inlet design to improve the performance of starting. Five inlets with different forebody surfaces are obtained by the method of characteristics based on a chin inlet and the starting processes of the five inlets are computed. Numerical simulations show that suitable surface can improve the starting performance. In this paper， the forebody which the transverse pressure gradient is set near the sidewall， leads to a reduction of self-start Mach number by 0.95. During the starting process， the shape of separation zone is rebuilt， which makes the spillage easier. What’s more， it is found that when closed separation zone is formed in the starting process， inlet starts at a higher Mach number than the design point， which should be avoided in inlet design. |
| Key words: Inlet Bump Inlet start Separation zone |
