Busemann进气道无粘流场数值分析

Inviscid CFD analysis of hypersonic Busemann inlet

关键词:  超音速冲压喷气发动机  Busemann进气道+  流线跟踪  数值仿真

Key words:  Supersonic combustion ramjet engine  Busemann inlet~+  Streamline traced  Numerical simulation

摘要:

为了研究Busemann进气道的流动特性,对设计马赫数为7的4种不同的Busemann进气道在Ma=4,5,6,7,8来流条件下进行了数值模拟和总体性能分析,对其中的3°截短流线跟踪进气道分析了攻角特性和侧滑角特性。研究表明:基准进气道具有相当高的无粘总压恢复;流线跟踪进气道在设计状态保持了基准进气道的高性能,而同时其起动性能大为提高;截短后的进气道长度大幅减小,而其性能仍然保持在较高的水平;截短流线跟踪进气道对带攻角或侧滑角飞行比较敏感。分析还表明,粘性造成了较大的总压损失。

Abstract:

Inviscid calculations were performed to study the performance of 2-D full Busemann inlet, 3-D square streamtraced inlet, truncated full inlet and truncated streamtraced inlet at various flight Mach numbers, and to study the performance of truncated streamtraced inlet at angles of attack and angles of sideslip, which were all designed for Mach 7 flight and have a same contraction ratio of 6. The influence of viscosity on the performance of full and truncated inlets was investigated preliminarily. The results show that the full Busemann inlet has very high inviscid total pressure recovery, streamline tracing technique is so perfect that the starting performance of streamtraced inlet is much better and its efficiency at the design point is as high as the full Busemann inlet. The truncated inlet is much shorter with low losses of performance. Truncated streamtraced inlet is sensitive to the flight at angles of attack or sideslip. Viscosity causes higher total pressure losses.