| 高超声速乘波飞行器气动实验研究 |
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| 引用本文： | 姚文秀,雷麦芳,杨耀栋,王发民.高超声速乘波飞行器气动实验研究[J].宇航学报,2002,23(6):82-85,90. |
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| 作者姓名： | 姚文秀 雷麦芳 杨耀栋 王发民 |
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| 作者单位： | 中国科学院力学研究所高温气体动力学重点实验室,北京,100080 |
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| 摘 要： | 以绕楔高超声速流场为基础，用流线追踪法生成了一种高超声速飞行器气动概念构形、初步探索了高超声速飞行器机身/推进系统一体化气动构形设计方法，开展了高超声速测压实验，结果表明：该类构形飞行器在高超声速飞行时，可以产生较高的升阻比，前体的预压缩效果明显，是以吸气式冲压发动机动力的有效途的飞行器构形。
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| 关 键 词： | 乘波飞行器 气动构形 气动实验 预压缩性能 |
| 文章编号： | 1000-1328(2002)06-0082-04 |
An aerodynamic experiment research of the hypersonic waverider vehicle |
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| YAO Wen xiu,LEI Mai fang,YANG Yao dong,WANG Fa min.An aerodynamic experiment research of the hypersonic waverider vehicle[J].Journal of Astronautics,2002,23(6):82-85,90. |
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| Authors: | YAO Wen xiu LEI Mai fang YANG Yao dong WANG Fa min |
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| Abstract: | The waverider shape to be used as a forebody on a airframe/engine integrated hypersonic vehicle is generated by a hypersonic flow round a wedge cone body.The lower surface of the waverider is created by trailing the stream line surface from the inlet plane until it intersects to the conic shock.Being an basic research,the design technique of airframe/engine integration bas been concerned.The surface pressure experiment has been done in a hypersonic wind tunnel.The results of experiment and computation show that the ratio of lift to drag( L/D =3 5)is good and the pre compressive ability of the foredody can satisfy the requirement of the inlet,So the configuration presented has a good future for scramjet engine vehicle. |
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| Keywords: | Waverider Dynamic configuration Aerodynamic experiment Pre compressive performance |
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