Flowfield characteristics in sidewall compression inlets

Xiang, Gaoxiang; Gao, Xiang; Jie, X. Z.; Li, Xudong; Li, Haoyang; Chen, Xiaopeng

doi:10.1007/s10409-020-00940-9

Cited by 11 publications

(1 citation statement)

References 42 publications

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“…The earlier studies conducted parametric studies by varying the major geometrical parameters such as cone angle or cowl leading-edge radius to get the desirable performance (Chen et al 2005a, b;Zha et al 1997). Hypersonic inlets have also been analyzed in the recent past (Chang et al 2009;Liang et al 2008;Nair et al 2005;Xiang et al 2020a) The analysis of 3D inlets with sidewall compression (Xiang et al 2020b) and the investigation of 3D shock interactions over wedges (Xiang et al 2021;Xiang et al 2016) provided a detailed study on the shock interaction problems in the intake flow field. A detailed aerodynamic analysis was conducted by Nair et al (Nair et al 2005) using Reynoldsaveraged Navier-Stokes to compute the flow through a hypersonic inlet.…”

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confidence: 99%

Flow Characteristics of a Mixed Compression Hypersonic Intake

2022

JAFM

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The flow field in a two-dimensional hypersonic mixed-compression inlet in a freestream Mach numbers of M∞ =2.0, 3.0, and 5.0 are numerically solved to understand the effect of throat area variation. The exit area ratio variation is simulated by placing a plug insert at different axial locations at the exit of the model. The flow field is achieved computationally by solving the Reynolds Averaged Navier-Stokes equations in a finite volume framework. For each flow condition, the variation in shock structure is analyzed and the variation of the oblique shock wave angle with the mass flow rate is calculated theoretically and compared with the present CFD analysis. The variation in oblique shock angle is calculated in terms of the mass flow rate by considering the capture area and spillage flow through the inlet. The theoretical results suggest that the method can predict the inlet operating conditions at different freestream Mach numbers and area ratios. This method can quantify the reduction in mass flow rate due to the throttling effect by analyzing the flow field shock pattern. The effects of various important performance parameters such as free stream Mach number, total pressure recovery, and mass flow ratio were then numerically investigated. As the Mach number is increased, the total pressure recovery is reduced, but the maximum value of the mass flow rate is increased. The analysis is also focused on the effect of throat area variation on performance parameters at each Mach number. The characteristic curve of the inlet is then obtained for each free stream Mach number.

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