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Accession number:        15708964（我注：此为检索号）
        Title:        Experimental Testing of a Hypersonic Inward Turning Inlet with Water-drop Like Shape to Circular Shape Transition
        Authors:        Yang Shunhua1; Liu Weixiong1; Le Jialing1; Wei Feng1; Zhang Wanzhou1; Chen Jun1
        Author affiliation:        1 Sci. & Technol. on Scramjet Lab., CARDC, Mianyang, China
        Source:        20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
        Publication date:        2015
        Pages:        1-10
        Language:        English
        ISBN-13:        978-1-62410-320-9
        Document type:        Conference article (CA)
        Conference name:        20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
        Conference date:        6-9 July 2015
        Conference location:        Glasgow, UK
        Publisher:        AIAA - American Institute of Aeronautics and Astronautics
        Place of publication:        Reston, VA, USA
        Material Identity Number:        YXB5-1901-395
        Abstract:        Wind-tunnel testing of a hypersonic inlet with shape transition has been conducted at Ma 6.5. The inlet has a water-drop like capture shape and a circle shape exit with the diameter of 70mm. A mechanical throttling is used to generate the back-pressure condition in present experiment. In order to increase the back pressure limit, boundary layer bleeding holes were also added to the model. The results showed that the max throttling limit before mechanically throttling induced unstart is about 70% without boundary layer bleeding, corresponding to the maximum back pressure approximately 180 times the free stream pressure. With the spillage holes, the max throttling limit before mechanically throttling induced unstart can be increased to about 86%. The present test demonstrated that this fixed geometry inlet with shape transition is a viable configuration for airframe-integrated scramj ets，

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