压力分布可控的高超声速进气道/前体一体化乘波设计

Integration waverider design of hypersonic inlet and forebody with preassigned pressure distribution

在二维弯曲激波高超声速进气道基础上,发展了一种压力可控的进气道/前体一体化乘波设计方法。通过事先指定前体/进气道壁面压力分布,结合二维特征线反设计方法,可以逆向设计出流向、横向压力分布规律都可控的进气道/前体外压缩段型面。采用该方法,设计了一种二维进气道/前体一体化方案,并对其进行数值模拟。结果表明:设计状态下,与不带侧板二维进气道相比,此类一体化方案中的进气道设计状态流量系数提高27%,出口压比提高48.5%,总压恢复系数提高10%;与楔导乘波理论设计的一体化方案相比,压力可控的一体化方案具有相似的外形尺寸和乘波特性,但进气道流量系数则较楔导乘波方案提高了5%,进气道出口压比提高6.4%,总压恢复系数提高2.3%。

On the basis of two-dimensional curved shock hypersonic inlets,a new integration,waverider design,of hypersonic inlet and forebody with preassigned pressure distribution is presented.A proper streamwise pressure distribution is assigned as the first step according to the shape of a curved shock wave.Afterwards,the external compression part of the inlet and forebody with controllable wall pressure distribution could be designed using the inverse two-dimensional method of characteristics.An integrated configuration is then derived from this concept and numerically studied.The results show that,on the design point,the flow capture ratio of the integrated configuration is enhanced by 27% compared with the pure two-dimensional inlet without sidewalls.The pressure ratio coefficient of inlet outflow rises by 48.5%,and the total pressure recovery coefficient is 10% higher than the no-sidewall inlet.In addition,compared with the Caret integration case,although with the same geometry shape and waverider character,the performance of mass flow rate,pressure ratio and total pressure recovery coefficient are 5%,6.4%,and 2.3%improved,respectively.