航天推进技术研究院主办
[1]南向军.宽马赫数二维曲面压缩高超声速进气道设计[J].火箭推进,2015,41(01):43-49.
NAN Xiang-Jun.Design of 2-D curved compression hypersonic inlet with wide Mach number range[J].Journal of Rocket Propulsion,2015,41(01):43-49.
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NAN Xiang-Jun.Design of 2-D curved compression hypersonic inlet with wide Mach number range[J].Journal of Rocket Propulsion,2015,41(01):43-49.
宽马赫数二维曲面压缩高超声速进气道设计
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
41
期数:
2015年01期
页码:
43-49
栏目:
研究与设计
出版日期:
2015-04-30
- Title:
- Design of 2-D curved compression hypersonic inlet with wide Mach number range
- Keywords:
- 2-D inlet; curved compression; wide operation range; bleeding on top
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 为设计出工作范围为Ma 2～7的RBCC发动机进气道，利用压升规律可控的二维曲面压缩设计方法，以Ma 6为设计点设计了宽马赫数新型二元高超声速进气道气动型面，采用前掠侧板减小了进气道的内收缩比，在Ma 4以下采用顶板放气的方式来扩展进气道的工作范围。数值模拟研究了进气道的流场及性能，发现采用曲面压缩设计的新型二元进气道在 Ma 4～7范围波系较少，流场结构良好，同时总压恢复较高，流量捕获能力强。通过顶板放气可实现在Ma 1.5～4范围内正常工作，放气量在15%以下。从流场和性能参数看，曲面压缩进气道在Ma 4以上性能良好，但在Ma 4以下流量捕获能力偏低。
- Abstract:
- Design method of 2-D curved compression with controlled pressure rise law is used to design a 2-D hypersonic inlet with wide operation range of Ma 2-7 at design point of Ma 6 for RBCC engine. A sweep forward side wall is used to reduce internal contraction ratio of inlet, and air bleeding slots are placed on top wall to expand operation range of inlet below Ma 4. Three dimensional numerical simulation is conducted in the range of Ma 1.5-7. The numerical results show that the new-type 2-D inlet with curved compression has less shock waves, good flow field structure and excellent performance in the range of Ma 4-7. With air bleeding on top wall, it can operate well in the range of Ma 1.5-4, and the air bleeding mass ratio is below 15%. Analysis turns out the curved compression inlet has high performance above Ma 4, but low mass capture capability below Ma 4.
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备注/Memo
收稿日期：2014-05-12；修回日期：2014-06-23 基金项目：国家863项目（2012AA702308） 作者简介：南向军（1985—），男，博士，研究领域为内流气体动力学
更新日期/Last Update:
1900-01-01