2022
DOI: 10.1016/j.ast.2021.107246
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Effects of boundary-layer bleed parameters on supersonic intake buzz

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Cited by 2 publications
(5 citation statements)
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“…With an increase in the freestream Mach number, the normal shock is strengthened, which promotes flow separation over the spike. Thus, the stability margin is affected since the intake buzz phenomenon is initiated earlier at higher mass flow rates and, therefore, at different operating conditions [36,37,62,90,91]. This is clearly depicted in Figure 7.…”
Section: Effect Of Mach Numbermentioning
confidence: 97%
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“…With an increase in the freestream Mach number, the normal shock is strengthened, which promotes flow separation over the spike. Thus, the stability margin is affected since the intake buzz phenomenon is initiated earlier at higher mass flow rates and, therefore, at different operating conditions [36,37,62,90,91]. This is clearly depicted in Figure 7.…”
Section: Effect Of Mach Numbermentioning
confidence: 97%
“…It is evident that a slot boundary layer bleed can significantly improve the intake performance and stability by preventing flow separation on the compression surface [58,91,108], especially when the shock train is close to the slot region [61,109]. Sethuraman et al [109] managed to reduce the shock oscillation by 50% with suction control, and reduced the oscillating frequency of the first shock by about 5 Hz, illustrating the effectiveness of the suction control when the shock train appears closer to the slot region [110].…”
Section: Boundary Layer Bleedmentioning
confidence: 99%
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