Beeinflussung viskoser Strömungseffekte in Hyperschall-Einläufen

摘要

For the performance of air-breathing hypersonic space planes, the proper design of the inlet system is of great importance. One of the dominating flow phenomena inside such hypersonic inlets is the mutual interaction of oblique shocks with boundary layers, often leading to a separation of the boundary layer from the inlet wall. In this work, several methods to manipulate shock / boundary layer interactions (for example boundary layer bleed or wall contouring) are investigated with regard to an application in hypersonic inlets. By means of analytical methods for the pre-dimensioning, computational fluid dynamics using a finite element method and experiments in the hypersonic wind tunnel facilities of the DLR (German aerospace center), favorable design parameters for these manipulation methods are presented. Finally, the most qualified methods are implemented in a hypersonic inlet model and the obtainable gain in inlet efficiency is demonstrated.