乘波前体三维内转进气道气动融合设计

Aerodynamic Combination Design Concept for Hypersonic Waverider Forebody and Inward Turning Inlet

关键词:  乘波前体  三维内转进气道  基本流场  斜激波  高超声速进气道

Key words:  Waverider forebody  Three-dimensional inward turning inlet  Basic flow field  Oblique shock wave  Hypersonic inlet

摘要:

在传统三维内乘波进气道设计方法的基础上，发展了一种具有乘波压缩特征的前体三维内转进气道气动融合设计方法。通过构造合适的双波入射基本流场，结合斜激波理论，可以推导出一种上游二维乘波流动叠加下游三维内收缩流动的基准流场。在此流场基础上进行流线追踪与气动融合设计，获得了一种乘波前体加三维内转进气道的气动布局方案。对该进气道方案数值模拟研究结果表明:在Ma6.0的设计状态下，该方案流量捕获系数能够达到0.96，总压恢复系数为0.53；而在Ma4.0的非设计状态，该方案流量捕获系数能够达到0.71，总压恢复系数为0.70。此外，与典型的前体二维混压进气道进行对比研究，乘波前体三维内转进气道方案总体性能提升明显，尤其是进气道流量捕获系数在设计状态下较二维方案上升了4.1%。

Abstract:

On the basis of the design concept of the traditional three-dimensional internal waverider inlet， an aerodynamic combination design concept of the forebody and three-dimensional inward turning inlet with the characteristic of waverider theory is presented. In combination with the flow field of two incident shock waves and the oblique shock wave theory， a flow field to give consideration to the two-dimensional flow in upstream and three-dimensional flow in the downstream is obtained. Afterwards， the aerodynamic combined surface of the inward turning inlet and waverider forebody could be designed by using the streamline traced method. A forebody/inlet configuration is subsequently derived from this concept and numerically studied. The results show that， at the design point (Ma6.0)， the mass flow rate of the inward turning inlet is 0.96， and the total pressure recovery is 0.53. In addition， at off-design points (Ma4.0)， the mass flow rate and the total pressure recovery are 0.71 and 0.70， respectively. Compared with the two-dimensional mixed compression inlet， the performance of aerodynamic combination configuration significantly improves. Especially， the mass flow rate at the design point increases by 4.1%.