Detailed analysis of a mixed compression hypersonic intake

Kurzfassung

An experimental study of the internal shock system of a series of inlet models is presented and discussed. The purpose of this experimental investigation was to evaluate the possibilities of influencing the shock/shock and shock/boundary layer interaction by the design of a suitable inlet geometry and thus avoiding bleed systems. In particulr, the occurrence of boundary layer separation was investigated. The wall pressure distribution is measured and compared to numerical results of CFD calculations. Another test series deals with the start behavior of the internal compression section of the mixed compression inlet. Therefore the development of the shock structure during intake start phases was investigated using a color-schlieren system and video recording. The air flow in the test section was slowly accelerated from zero to Mach 3.0, and the shock system was recorded.