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In the present work, two streamline-traced inlets (STIs) are designed to achieve high total pressure recovery and volumetric efficiency for flights operating at a Mach number of 3. An in-house code, based on the method of characteristics and gradient-descent optimization, is employed to determine the contour surfaces of the STIs that optimize the compression process at design conditions. The flowfield and performance of standalone STIs are analyzed through computational simulations over a freestream Mach number range of 2.9–3.4. Furthermore, the integration of STIs with rotating detonation engines (RDEs) is investigated for high-speed propulsion systems. The performance of the integrated STI/RDE systems is evaluated using a low-order analytical model. The results reveal that the performance metrics of the STI/RDE systems either match or surpass those of a previous osculating inlet design across a range of flight Mach numbers.

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Streamline-Traced Inlet Design and Integration with Rotating Detonation Engines

  • 会议论文

  • 发表日期：

    2025年

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  • Liwei Zhang,
  • Malcolm Branch,
  • Frank Lu

摘要

In the present work, two streamline-traced inlets (STIs) are designed to achieve high total pressure recovery and volumetric efficiency for flights operating at a Mach number of 3. An in-house code, based on the method of characteristics and gradient-descent optimization, is employed to determine the contour surfaces of the STIs that optimize the compression process at design conditions. The flowfield and performance of standalone STIs are analyzed through computational simulations over a freestream Mach number range of 2.9–3.4. Furthermore, the integration of STIs with rotating detonation engines (RDEs) is investigated for high-speed propulsion systems. The performance of the integrated STI/RDE systems is evaluated using a low-order analytical model. The results reveal that the performance metrics of the STI/RDE systems either match or surpass those of a previous osculating inlet design across a range of flight Mach numbers.