Length scale for the estimation of buzz frequency in the limit of high mechanical blockage in mixed-compression intakes

Devaraj, Manoj Kumar K.; Jutur, Prahallada; Rao, Srisha M. V.; Jagadeesh, G.; Anavardham, Ganesh T.K.

doi:10.1017/jfm.2021.230

Cited by 3 publications

(1 citation statement)

References 19 publications

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“…Moreover, in a study of unignited behaviour caused by subsonic leakages inside a hypersonic inlet at Mach 6 with a throttling ratio of 0 to 0.69, the intake began to exceed Kantrowitz limitations despite being less than the isentropic limits [12]. Researchers suggested that it is vital to analyse shock train oscillations in order to prevent non-ignition intake situations [13][14][15][16].…”

Section: Introductionmentioning

confidence: 99%

Assessing the Performance of Hypersonic Inlets by Applying a Heat Source with the Throttling Effect

et al. 2022

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Utilization of a heat source to regulate the shock wave–boundary layer interaction (SWBLI) of hypersonic inlets during throttling was computationally investigated. A plug was installed at the intake isolator’s exit, which caused throttling. The location of the heat source was established by analysing the interaction of the shockwave from the compression ramp and the contact spot of the shockwave with that of the inlet cowl. Shockwave interaction inside the isolator was investigated using steady and transient cases. The present computational work was validated using previous experimental work. The flow distortion (FD) and total pressure recovery (TPR) of the inflows were also studied. We found that varying the size and power of the heat source influenced the shockwaves that originated around it and affected the SWBLI within the isolator. This influenced most of the performance measures. As a result, the TPR increased and the FD decreased when the heat source was applied. Thus, the use of a heat source for flow control was found to influence the performance of hypersonic intakes.

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Section: Introductionmentioning

confidence: 99%

Assessing the Performance of Hypersonic Inlets by Applying a Heat Source with the Throttling Effect

et al. 2022

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Leading-edge bluntness effects on the hypersonic flow over the double wedge at multiple aft-wedge angles

Ray

2023

Physics of Fluids

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The present numerical investigation focuses on the leading-edge bluntness effects on the double wedge with varied aft-wedge angles exposed to low enthalpy hypersonic free stream conditions. The bluntness ratio in this study varies, ranging from R/L1 = 0 (sharp leading edge) to R/L1 = 0.577 (maximum allowable bluntness), along with the aft-wedge angle varying between θ2 = 45° and 60°. Noticeably, even a small bluntness ratio can completely change the shock interaction pattern compared to its sharp geometrical counterpart due to a detached leading-edge shock, enlarged separation bubble, and location of various shock waves concerning it. Critical bluntness ratios exist for the low aft-wedge θ2 = 45° angle, but increasing the aft-wedge angle makes the flow field highly unsteady for some bluntness ratios. Nevertheless, these bluntness ratios for such double-wedge configurations are reported using the mean of separation bubble size. Moreover, this work unravels the cause of such unsteadiness for the unsteady flow fields using the spatial-temporal evolution of the wall pressure distribution and fast Fourier transform of the pressure fluctuation signal at the compression corner and supports the deduced observation with the help of energy-based proper orthogonal decomposition. The increased shock–boundary layer interaction strength moves the separation point upstream beyond the junction of cylindrical bluntness and inclined fore-wedge surface, accompanying sudden change in its direction of motion that perturbs the shear layer that set to a self-sustained, highly unsteady flow field.

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Performance of the Hypersonic Intake in Varied Free-Stream Conditions

Ray

2023

25th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Length scale for the estimation of buzz frequency in the limit of high mechanical blockage in mixed-compression intakes

Abstract: Abstract

Cited by 3 publications

References 19 publications

Assessing the Performance of Hypersonic Inlets by Applying a Heat Source with the Throttling Effect

Assessing the Performance of Hypersonic Inlets by Applying a Heat Source with the Throttling Effect

Leading-edge bluntness effects on the hypersonic flow over the double wedge at multiple aft-wedge angles

Performance of the Hypersonic Intake in Varied Free-Stream Conditions

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