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- W2392173170 abstract "Different leading edge shock on hypersonic curved ramp two-dimensional inlet directly influences the inlet performance,specially,the flow coefficient.A detailed analysis and investigation was performed on the variation characteristics of leading edge shock generated by two different inlets response to the variation of inlet attack angle and inflow Mach number.The calculation results reveal that for wedge-isentropic two-dimensional inlet,the angle between the leading edge shock and compression surfaces decreases in advance,then increases with increase of the inlet attack angle.However,the angle always decreases with the increase of the free stream Mach number,whereas,for two-dimensional hypersonic curved shock compression inlet with the law of constant pressure gradient,the angle between the leading edge shock and compression surfaces decreases with increase of both the attack angle and the free stream Mach number.According to theory and calculation analysis,different oblique shock and Mach wave interaction mode causes different characters of leading edge shock generated by two different inlets response to the variation of inlet attack angle and inflow Mach number." @default.
- W2392173170 created "2016-06-24" @default.
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- W2392173170 date "2013-01-01" @default.
- W2392173170 modified "2023-09-25" @default.
- W2392173170 title "Analysis of Leading Edge Shock on Hypersonic Curved Ramp Two-Dimensional Inlet" @default.
- W2392173170 hasPublicationYear "2013" @default.
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