Study on a Two-Dimensional Supersonic Inlet with Inner Profile Adjustment
نویسندگان
چکیده
According to the requirements of a wide speed range, variable-geometry supersonic inlet with inner surface adjustment is studied. The basic design model established, and influence profile on resisting back pressure ability performance boundary are analyzed using theoretical method. Based numerical simulation method, flow field carried out, parameter distribution studied in comparison fixed-geometry scheme. results show that starting Mach number not changed for two schemes because they have same during low-speed flight. has insufficient compression incoming flow, decreases significantly high-speed ratio wave system can be easily at time through adjustable Both analysis improved after adjustment. As such, method this paper fundamentally solve problem wide-range working flight, realized.
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ژورنال
عنوان ژورنال: Energies
سال: 2022
ISSN: ['1996-1073']
DOI: https://doi.org/10.3390/en15145057