超额定状态下二元超声速进气道的流动特性

饶彩燕; 谭慧俊; 张启帆

doi:10.13224/j.cnki.jasp.2017.05.017

超额定状态下二元超声速进气道的流动特性

doi: 10.13224/j.cnki.jasp.2017.05.017

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，南京 210016

基金项目: 江苏省普通高校研究生实践创新计划项目（SJLX15_0106）；中央高校基本科研务费专项资金；国家自然科学基金(11172136,11172133,11532007)；江苏省高校优势学科建设工程资助项目

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出版历程
- 收稿日期: 2015-06-14
- 刊出日期: 2017-05-28

Flow characteristics of a rectangular supersonic inlet under over-speed state

摘要

摘要: 为了揭示超额定工作状态下超声速进气道内的复杂流动机理，对一设计马赫数为2.0的二元超声速进气道开展了数值模拟研究，获得了其在不同来流马赫数状态、不同节流状态下的流场结构.结果表明：当进气道工作在额定状态时，随着节流程度的增加，其激波串的核心区由偏向下壁面摆至偏向上壁面；而在超额定状态下，由于依次受到唇罩内侧分离包、唇罩激波等的影响，激波串核心区则由偏向上壁面转而摆至偏向下壁面.在来流马赫数为2.5的节流状态下，其唇罩激波与前体斜激波相交形成了马赫杆等复杂波系结构，而来流马赫数为3.0状态却并未形成此类现象.在上述两种超额定工作状态下，前体斜激波的上透射激波均在高反压条件下演化为正激波形态，而唇罩激波的下透射激波形态也发生了明显的改变.
- 超额定 /
- 超声速进气道 /
- 激波串 /
- 马赫杆 /
- 核心区
Abstract: To aid in understanding the flow mechanism in supersonic inlet under the over-speed state, a numerical simulation was performed to obtain the flow structure of a rectangular inlet whose design Mach number was 2.0, operating under different inflow Mach numbers and backpressures. Results indicate: for the design case of Mach number 2.0, the core flow of shock train was deflected from the cowl-side surface to the ramp-side surface associated with the backpressure increase. While the inlet operated under the over-speed state, the core flow of shock train was deflected to the ramp-side surface firstly and then to the cowl-side surface due to the effects of the cowl-lip separation bubbles and the cowl shock in turn. For the case of inflow Mach number 2.5, a Mach-stem appeared at the joint point between forebody oblique shock and cowl shock once the backpressure increaseed to a certain value. However, this flow structure didnt appear in the case of inflow Mach number 3.0. Under the above two over-speed states, with the increase of backpressures, the transmit shock of forebody oblique shock was transformed into normal shock, and the transmit shock of cowl shock also changed its shape.
- over-speed /
- supersonic inlet /
- shock train /
- Mach-stem /
- core flow

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参考文献(18)

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