Abstract
The poor self-starting ability at low Mach number normally restricts the proper operation of hypersonic inlets within a wide Mach-number range. A fluidic control method with backflow duct based on the flowfield characteristics of the unstart flows is brought forward and investigated through a combination of computational and experimental methods. First, the uncontrolled case is studied. Results show that the baseline inlet does not start until Mach 6.1, which is too high for the researched hypersonic inlet. Then, the controlled case demonstrates that the flow separation is well controlled by means of the closed flow cycle introduced by the backflow duct. Numerical investigations indicate that the self-starting Mach number of the backflow-duct inlet declines to Mach 4.3, and starting status at Mach 5.0 and is observed experimentally. The self-starting ability of the inlet is improved remarkably; meanwhile, at high Mach numbers, the flow structure is barely impacted by the minimal backflow rate, ensuring the high-performance operation of hypersonic inlets.
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