Studies of scramjet/airframe integration techniques for hypersonic aircraft
Studies of scramjet/airframe integration techniques for hypersonic aircraft
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DOI：
10.2514/6.1975-58
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发表时间：
1975
期刊：
影响因子：
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通讯作者：
C. L. Edwards;W. J. Small;J. P. Weidner;P. J. Johnston
中科院分区：
文献类型：
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作者：
C. L. Edwards;W. J. Small;J. P. Weidner;P. J. Johnston
在最近的高超声速飞行器设计研究中，采用了新的发动机-机体一体化设计和分析技术。发展了一种新技术来设计飞行器的前体，以便在进气道入口处产生均匀的预压缩流。结果与三维特性计算进行了验证。计算喷管流的新的三维方法的结果表明，飞行器的整个下后体都可以用作超燃冲压发动机的排气喷管，以在很宽的飞行条件范围内实现高效、可控和稳定的飞行。
New design and analysis techniques for engine-airframe integration were applied in a recent hypersonic vehicle design study. A new technique was developed to design the vehicle's forebody so that uniform precompressed flow was produced at the inlet entrance. Results are verified with three-dimensional characteristic calculations. Results from a new three-dimensional method for calculating nozzle flows show that the entire lower afterbody of the vehicle can be used as a scramjet exhaust nozzle to achieve efficient, controlled, and stable flight over a wide range of flight conditions.