Based on the equal-intensity shock theory, this article designed a supersonic inlet working in Mach number 3.0∼5.5 with the background of an air-breathing engine. The inlet applied the four-shock train mixed compression configuration and inserted a sidewall compression at the beginning of the isolator. Through developing effective 3D RANS computations validated by current experiments, the performance of the designed inlet was identified. The designed inlet self-starts at freestream Mach number Ma = 3.0 under which the total pressure recovery coefficient has dramatic increment, and the aerodynamic choking at the inlet throat no longer presents; the inlet keeps working at all studied flight states with zero angle of attack (AoA) and achieves shock-on-lip at the design point Ma = 5.0. Both positive and negative AoAs can disrupt the equal-intensity shock allocations, which degrade the inlet performance. The inlet obtains maximum total pressure recovery coefficient at zero AoA. The maximum back pressure at Ma = 3.0∼5.5 obtained by the inlet surpasses the requirements and keeps a certain margin. The inlet performance basically meets all the goals proposed by the engine.


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    Title :

    Numerical analysis on the conceptual design of an air-breathing engine inlet working in mach number 3∼5.5


    Contributors:
    Huo, Chao (author) / Yang, Zhenhua (author) / Zhang, Zhengze (author) / Liu, Peijin (author)


    Publication date :

    2022-02-01


    Size :

    14 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English







    NUMERICAL INVESTIGATIONS OF INLET-COMBUSTOR INTERACTIONS FOR A SCRAMJET HYDROGEN-FUELED ENGINE AT A MACH FLIGHT NUMBER OF 8

    Santana, E.R. / Weigand, B. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2012