| 波瓣式主喷管排气引射系统的高速冷态推力特性试验研究 |
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| 引用本文： | 李黎,吴寿生.波瓣式主喷管排气引射系统的高速冷态推力特性试验研究[J].航空动力学报,1997,12(4):429-432. |
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| 作者姓名： | 李黎 吴寿生 |
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| 作者单位： | 1.北京航空航天大学热动力研究所 |
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| 摘 要： | 对基准圆柱收敛喷管、五种波瓣主喷管、以及波瓣主喷管与带扩压段的混合管和不带扩压段的混合管所组成的不同排气引射系统进行了推力随喷管前压力(0.15～0.5MPa)变化的特性试验。试验结果表明:波瓣主喷管排气引射系统在高速排气条件下也具有较好的应用前景；但在设计上,必须考虑高速,尤其是超音排气的气动特点所带来的相关问题。
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| 关 键 词： | 引射喷管 推力喷管特性 高速 |
| 收稿时间： | 2/1/1997 12:00:00 AM |
| 修稿时间： | 5/1/1997 12:00:00 AM |
THRUST CHARATERISTICS OF EXHAUST EJECTOR SYSTEMS WITH LOBED NOZZLES TESTED AT COLD HIGH SPEED CONDITIONS |
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| Li Li and Wu Shousheng.THRUST CHARATERISTICS OF EXHAUST EJECTOR SYSTEMS WITH LOBED NOZZLES TESTED AT COLD HIGH SPEED CONDITIONS[J].Journal of Aerospace Power,1997,12(4):429-432. |
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| Authors: | Li Li and Wu Shousheng |
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| Institution: | 1.4th Dept.Beijing University of Aeronautics and Astronautics,Beijing 1000832.4th Dept.Beijing University of Aeronautics and Astronautics,Beijing 100083 |
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| Abstract: | A set of thrust charateristics (thrust with nozzle pressure)of a round covergent nozzle、five lobed nozzles and lobed nozzle-mixing tube combinations with and without difffusers have been obtained from the experimental investigation at cold high speed conditions (nozzle pressure=0.15～0.5 MPa) Test results show that the lobed nozzles of the exhaust ejector systems at high speed conditions also have superior application prospects,provided their designs consider the impact of high speed flow,in especial,the aerodynamic charateristics of supersonic exhaust flow. |
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| Keywords: | Nozzles with injector Thrust characteristics High speed |
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