Journal of Propulsion and Power · 2007 · 40 citations · 5 references
EngineeringAerospace EngineeringPhysicsAerodynamicsFluid DynamicsPropulsionAerodynamic TestingExperimental AerodynamicsRamjet EnginesRamjet PropulsionSupersonic AerodynamicsUnsteady AerodynamicsBleedMach NumberRamjet PerformanceShock - Boundary-layer InteractionShock Boundary-layer InteractionShock-boundary Layer InteractionShock-boundary-layer InteractionSupersonic Flow
The experiments aimed to understand how different geometry variations affect the performance and unsteady behavior of a ramjet intake, seeking an optimum design. The study used a trisonic windtunnel at the German Aerospace Center to test a Ma = 2.5 ramjet with four bleed configurations, measuring pressure, temperature, mass flow, and capturing high‑speed Schlieren images. The results showed that varying the geometry and bleed configuration influenced the intake’s performance and unsteady behavior, allowing the identification of an optimum design.
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 windtunnel 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 Ma = 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 was 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.
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Supersonic-inlet boundary-layer bleed flow
G. J. Harloff, Gregory E. Smith · AIAA Journal · 1996 · 88 citations · Full text