摘要
超燃冲压发动机尾喷管与燃烧室直接相连,由于没有几何喉道和收缩段的整流作用,实际尾喷管的进口气流是非均匀的。为了研究非均匀进口对超燃冲压发动机尾喷管性能的影响,以非均匀马赫数分布为目标,设计了非均匀出口风洞,并进行了风洞出口流场校核试验,试验校核得到的马赫数与目标值的最大偏差只有1.95%。在此基础上,进行了非均匀进口对超燃冲压发动机尾喷管气动性能影响的数值模拟研究,并进行了相应的风洞试验,试验与数值模拟结果吻合良好,验证了数值模拟结果的准确性。研究结果表明,非均匀进口会造成尾喷管推力下降2.92%～5.02%、负升力增加可达17.2%、俯仰力矩减小4.2%～6.7%。
A scramjet nozzle is directly connected to the combustor and there is no contraction section or throat, which makes the nozzle entrance flow nonuniform. In order to learn the influence of the nonuniform entrance flow on the nozzle per- formance, wind tunnel nozzles are designed on nonuniform Mach number distribution of the exit flow, and verification tests in- dicate that the exit flow of the wind tunnel nozzles rather perfect for later experiments and the maximum deviation of Mach number from the trarget value is only 1.95%. Then, experiments on scramjet nozzle nonuniform entrance flow show that the numerical study is accurate. Detailed numerical research on the nonuniform entrance flow of a scramjet nozzle is done which shows that the nonuniform entrance flow of the scramjet nozzle would reduce the thrust by 2.92 %-5.02 %, increase negative lift up to 17.2% ,and decrease pitch moment by 4.2%-6.7%.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2013年第10期2308-2315,共8页
Acta Aeronautica et Astronautica Sinica
关键词
超燃冲压发动机
单边膨胀喷管
气动性能
数值模拟
风洞试验
scramjet
single expansion ramp nozzle
aerodynamic performance
numerical simulation
wind tunnel experi-ment
