The design and flow field simulation of single expansion ramp nozzle with variable flaps
The design and flow field simulation of single expansion ramp nozzle with variable flaps
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发表时间：
2009
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通讯作者：
Wang Zhanxue
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作者：
Wang Zhanxue
对于高超声速飞行器，喷管气动特性对飞行器性能影响很大。基于特征线法，考虑变比热和边界发展的影响，开发了确定高超声速飞行器单膨胀斜坡喷管外形的方法和程序。利用CFD数值模拟技术，计算了设计点和飞行轨迹上的喷管流场和气动特性。结果表明，在马赫数为5，即设计点时，所设计的单膨胀斜坡喷管性能较好，但在大部分低、中超音速飞行状态下，单膨胀斜坡喷管的性能较好。为了改善单膨胀斜坡喷管的变工况性能，研究了整流罩角度对喷管性能的影响，结果表明，调整罩倾角可以改善单膨胀斜坡喷管的变工况性能。
For hypersonic vehicles,the effect of nozzle aerodynamic characteristics on vehicles per-formance is serious.Based on Characteristic methods,considering effect of variable specific heat and boundary development,the methods and program for determining contour of single expansion ramp nozzles for hypersonic vehicles were developed.With CFD numerical simulation technology,The nozzle flow field and aerodynamic characteristics were computed on design point and along flight trajectory.The results in-dicated that,at Mach 5,namely design point,the performance of designed single expansion ramp nozzles is perfect,but throughout much of the low-supersonic and mid-supersonic flight regime,the performance was poor.Flow separation was observed on the expansion ramp at Mach 2.5.To improve off-design performance of single expansion ramp nozzles,the effects of cowl angle on nozzle performance were studied.The results indi-cated that adjustments of cowl angle could improve off-design performance of single expansion ramp nozzles.