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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2023, Vol. 44 ›› Issue (12): 127857-127857.doi: 10.7527/S1000-6893.2022.27857

• Fluid Mechanics and Flight Mechanics • Previous Articles    

Design of inward turning inlet with controlled Mach number under non-uniform inflow

Yongzhou LI1(), Di SUN1, Renhua WANG2, Kunyuan ZHANG3   

  1. 1.College of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China
    2.AECC Aero Engine Control System Institute,Wuxi 214063,China
    3.College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
  • Received:2022-07-26 Revised:2022-08-03 Accepted:2022-08-26 Online:2022-09-14 Published:2022-09-13
  • Contact: Yongzhou LI E-mail:nuaa-2004@126.com
  • Supported by:
    National Natural Science Foundation of China(11702205);Jiangxi Province Innovation Leading Talent Project;Open Fund for Key Laboratory of Aeroengine Thermal Environment and Thermal Structure(CEPE2022005);Natural Science Foundation of Chongqing(cstc2020jcyj-msxmX0823)

Abstract:

A design method of the inward turning inlet with controlled Mach number distribution under non-uniform inflow is proposed to meet the integrated design requirements of waverider and inlet of the hypersonic vehicle with the abdominal intake layout. The axisymmetric basic flow field is designed inversely by the rotational method of characteristics under the conditions that the Mach number distribution of the inflow and the wall are given at the same time. The inward turning inlet with the circular intake is designed by the streamline tracing technology and compared with the traditional inward turning inlet based on the uniform inflow. The numerical simulation results show that the basic flow field structure of the non-uniform inflow is consistent with expectation, which can control the Mach number distribution of the entire flow field, and its compression efficiency is higher than that of the traditional uniform inflow. The inlet with non-uniform inflow can maintain the wave structure of the basic flow field and capture the full flow at the deign point. The overall performance of the inlet with non-uniform inflow under viscous conditions is satisfactory and higher than that of the inlet with uniform inflow under the same inflow condition. Therefore, the design method is feasible and provides an innovative approach for hypersonic foredody/inlet integrated design.

Key words: hypersonic inlets, non-uniform inflow, basic flowfield, Mach number, integrated design, streamline tracing

CLC Number: