摘要
为研究等离子体流动控制在乘波体前体/发动机一体化设计中的应用,设计了二波系前体,首先研究不同工况下前体的性能,然后比较不同等离子体控制方法对非设计点总压恢复系数等参数的影响。研究表明,非设计点工况下前体激波不再满足激波-唇口原则,马赫数降低会使预压能力下降和流量系数减小,马赫数增大会使总压损失增大。马赫数小于设计点时,MHD方法效果较差,此时,等离子体虚拟前沿能够使减小总压损失、提高预压能力、增大空气捕获量。马赫数大于设计点时,准直流放电等离子体欧姆加热效应可减小总压损失,但会使预压能力下降和空气捕获量减小,此时MHD方法可以提高预压能力、增大空气捕获量,但会使总压损失急剧增大。
An inlet of waverider formed by two step wedge was design to investigate the application of plasma flow control on the airframe/scramjet integration design of waverider.First the performance parameters of this inlet was investigated at different condition,then the effects,such as total pressure recovery coefficient of different kinds of plasma flow control to the cases of off-design was studied.The results show that,the shock-on-lip condition can not be met at Mach numbers higher or lower the design Mach number.At Mach numbers lower than the design value,a portion of the air compressed by the shock misses the inlet and the air mass capture decreases.At Mach numbers higher than the design value,the total pressure recovery coefficient will increase.At Mach numbers lower than the design value,the effects of MHD flow control method is invalid,but the effects of virtual cowl flow control method is very well,the total pressure recovery coefficient,the compression rate and the flow coefficient of inlet will increase.At Mach numbers higher than the design value,ohmic heating flow control of quasi-DC electrical discharge will decrease total pressure recovery coefficient,but the compression rate and the flow coefficient of inlet will decrease.MHD flow control method will increase the compression rate and the flow coefficient of inlet,but the total pressure recovery coefficient will decrease sharply.
出处
《飞机设计》
2012年第5期7-12,共6页
Aircraft Design
