航天推进技术研究院主办
[1]李永洲,李光熙,张堃元,等.进口水平投影可控的流线追踪内收缩进气道设计[J].火箭推进,2017,43(03):28-34.
LI Yongzhou,LI Guangxi,ZHANG Kunyuan,et al.Design on streamline tracing inward turning inlet with controlled horizontal projection of intake[J].Journal of Rocket Propulsion,2017,43(03):28-34.
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LI Yongzhou,LI Guangxi,ZHANG Kunyuan,et al.Design on streamline tracing inward turning inlet with controlled horizontal projection of intake[J].Journal of Rocket Propulsion,2017,43(03):28-34.
进口水平投影可控的流线追踪内收缩进气道设计
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
43
期数:
2017年03期
页码:
28-34
栏目:
研究与设计
出版日期:
2017-08-01
- Title:
- Design on streamline tracing inward turning inlet with controlled horizontal projection of intake
- Keywords:
- hypersonic; inward turning inlet; streamline tracing; horizontal projection; inverse design
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 为了满足两侧进气布局飞行器的乘波前体与进气道一体化设计要求，提出了一种进口水平投影可控的流线追踪内收缩进气道设计方法。基于马赫数分布可控的轴对称基准流场，在指定进口水平投影为椭圆的条件下，采用该方法设计了内收缩进气道并在设计点(Ma=5.4)和接力点(Ma=4.0)对其进行数值研究。结果表明，设计点时进气道都能保持基准流场的波系结构和沿程压力分布，无粘时可以全捕获自由来流，喉道性能与基准流场几乎相等。有粘条件下，设计点和接力点时进气道具有较高的压缩效率和良好的流量捕获能力，接力点的流量系数高达0.85。该设计方法为内收缩进气道与乘波前体的一体化设计提供了新途径。
- Abstract:
- A design method has been presented for streamline tracing inward turning inlet with controlled horizontal projection of intake in order to meet the integrated design requirements of waverider forebody and inlet with both sides intake configuration vehicle. Based on the axisymmetric basic flowfield with controllable Mach number distribution, the inward turning inlet is designed with an elliptical horizontal projection of intake utilizing this method. Numerical simulation is conducted at design (Ma=5.4) and relay point (Ma=4.0). The results indicate that the inlet can retain wave structure and pressure distribution of basic flowfield, and capture all of free incoming flow on the inviscid condition at design point. Its performance of throat plane is almost equal to basic flowfield. On the viscous condition, the inlet has high compression efficiency and flow capture ratio at design and relay point. The flow coefficient is 0.85 at relay point. The design method provides a new approach for the integrated design of inward turning inlet and waverider forebody.
参考文献/References:
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相似文献/References:
[1]杜炜强,吴宝元.高超声速进气道优化设计初探[J].火箭推进,2007,33(06):17.
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备注/Memo
收稿日期：2017-03-30；修回日期：2017-04-13 基金项目：基础科研计划（JCKY2016203C050） 作者简介：李永洲（1984—），男，博士，工程师，研究领域为高超声速组合发动机设计
更新日期/Last Update:
1900-01-01