2013
DOI: 10.2514/1.j052384
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Unsteady Behaviors of a Hypersonic Inlet Caused by Throttling in Shock Tunnel

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Cited by 104 publications
(45 citation statements)
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“…The experiments were conducted in the KDJB330 shock tunnel of the University of Science and Technology of China with a free-stream Mach number M ∞ = 6 (Li et al 2013(Li et al , 2018Zhang et al 2019b). The stagnation pressure and temperature of the incoming flow were 1.4 MPa and 830 K, respectively, corresponding to a free-stream unit Reynolds number of approximately 4.2 × 10 6 m −1 .…”
Section: Methodsmentioning
confidence: 99%
“…The experiments were conducted in the KDJB330 shock tunnel of the University of Science and Technology of China with a free-stream Mach number M ∞ = 6 (Li et al 2013(Li et al , 2018Zhang et al 2019b). The stagnation pressure and temperature of the incoming flow were 1.4 MPa and 830 K, respectively, corresponding to a free-stream unit Reynolds number of approximately 4.2 × 10 6 m −1 .…”
Section: Methodsmentioning
confidence: 99%
“…During the big buzz process, the external-compression shock system is circularly destroyed and reestablished, and the induced separation shock exhibits a large-amplitude oscillatory motion. The downstream throttling device can be used to initiate the unstart of the hypersonic inlet [20] and keep the flow mode in the starting condition, little buzz cycle, and big buzz cycle at low, moderate, and high throttling ratios, respectively. Numerous studies [4] have demonstrated the ability to capture the flow field dynamics in unstarted hypersonic inlets and the importance of alleviating the negative effects in hypersonic vehicle design.…”
Section: Introductionmentioning
confidence: 99%
“…To date, nearly all the unstart detection techniques are based on high-frequency pressure measurements [20][21][22][23]. However, the term "unstart" is used to denote operation under conditions where flow phenomena in the internal portion of the inlet alter its capture characteristics [23].…”
Section: Introductionmentioning
confidence: 99%
“…In this study, the shock tunnel operated under an equilibrium interface mode, and the available test time was approximately 20 ms [20]. The total pressure and temperature at the equilibrium interface condition were p t 1.3 MPa and T t 940 K, respectively, corresponding to a freestream unit Reynolds number of approximately 4.0 × 10 6 ∕m, which were estimated using the incident shock Mach number measured by two piezoelectric-type pressure transducers mounted 1 m apart near the end of the driven tube and the given filling conditions of the driven tube.…”
Section: A Facility and Test Modelmentioning
confidence: 99%