| description abstract | The flow compression process design is critical for enhancing the efficiency and overall performance of hypersonic airbreathing propulsion. Many studies have sought to solve the challenging problems that inlet design presents, such as enhancing performance at off-design points, minimizing total pressure loss, and shortening the length. In this case, an inverse design approach for curved surfaces is proposed, which generates the entire compression flow field with a certain wall Mach number distribution as well as the molded line of the compression surface. In contrast to traditional flow compression modes, the proposed technique significantly increases design space and flexibility. Curved surfaces with a specific wall Mach number linear distribution along the flow direction are examined in this work. The flow compression process is made more efficient by using the inverse design approach. The curved surface compresses the flow primarily by isentropic compression and supplementary shock compression, and the entire wall surfaces participate in this process. In particular, the ratios of shock compression and isentropic compression can be changed as necessary. The result is a compromise between classical isentropic compression and multiramp compression. To illustrate the benefit, the incorporating of curved surface with sidewall compression inlet was evaluated and verified in wind tunnel tests. Mach number and pitot pressure profiles in the isolator’s exit cross section and wall pressure distributions were utilized to study the flow field. The application provides a more flexible method and achieves the objective of functioning in a broad range of Mach numbers, according to the results. The experimental findings were found to be in accordance with the projected inlet performance. | |
