Experimental investigations of the performance and unsteady behavior of a supersonic intake

The performance and the unsteady behavior of a ramjet intake model have been investigated. The investigation was carried out in the supersonic flow range of the trisonic wind tunnel of the German Aerospace Center. These experiments were conducted to understand the complex flow phenomena of the ramjet intake and the effects on the performance. The experiments were carried out on a ramjet designed for a shock on lip Mach number of M = 2.5. To study the effect of the shock boundary layer interaction on the performance, four different bleed configurations of the boundary layer were used. The effect on performance and the unsteady behavior of each geometry variation were investigated and compared to find the optimum intake design. Pressure and temperature measurements were taken of the performance and the unsteady behavior using mass flow determination and shown with high-speed schlieren photographs.