Three-dimensional viscous analysis of a Mach 5 inlet and comparison with experimental data

Reddy, D. R.; Weir, Lois J.

doi:10.2514/3.23496

Cited by 14 publications

(4 citation statements)

References 5 publications

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“…The module was designed to study the flow structure, to obtain the inlet characteristics, and to study the mutual effects of the combustion of the inlet. Reddy and Weir 6 carried out numerical calculations of the flow field in the Mach No. 5 inlet using the PARC3D code and compared the results with the experimental data.…”

Section: Falempin and Montazelmentioning

confidence: 99%

Numerical Simulations of Flow in a 3-D Supersonic Intake at High Mach Numbers

Sivakumar¹,

Babu²

2006

DSJ

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Numerical simulations of the compressible, 3-D non reacting flow in the engine inlet section of a concept hypersonic air-breathing vehicle are presented. These simulations have been carried out using FLUENT. For all the results reported, the mesh has been refined to achieve areaaveraged wall y+ about 105. Mass flow rate through the intake and stagnation pressure recovery are used to compare the performance at various angles of attack. The calculations are able to predict the mode of air-intake operation (critical and subcritical) for different angles of attack. Flow distortion at the intake for various angles of attack is also calculated and discussed. The numerical results are validated by simulating the flow through a 2-D mixed compression hypersonic intake model and comparing with the experimental data.

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Section: Falempin and Montazelmentioning

confidence: 99%

Numerical Simulations of Flow in a 3-D Supersonic Intake at High Mach Numbers

Sivakumar¹,

Babu²

2006

DSJ

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“…Knight et al 24 in their summary of canonical SWBLI studies till 2000 concluded that the RANS approach is capable of predicting the mean variables for weak to moderate SWBLIs and, however, fails to predict the strong SWBLIs as well as the unsteady nature. Similarly, several intake simulations [25][26][27][28][29][30] have shown that the wall static pressure prediction indicates some discrepancy downstream of the isolator due to the inability of turbulence models to capture the flow separation as well as the unsteadiness accurately. However, most of these studies have used Baldwin-Lomax or some variants of k-ε turbulence models.…”

Section: Introductionmentioning

confidence: 99%

Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Pattnaik

Rajan

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Results of numerical investigation of flow and performance characteristics of a rectangular supersonic intake experimentally tested at Mach number of 4.03 are presented. The viscous flowfield has been obtained by solving Favre averaged Navier–Stokes equations with two eddy viscosity turbulence models, namely, Mentor’s baseline (BSL) k-ω and shear stress transport (SST) k-ω models. In addition, the effect of wall temperature conditions as well as several configurations of cowl and isolator are simulated to validate the computational methodology. The analysis has been carried out at a freestream Mach number of 4.03 and 0° angle-of-attack, corresponding to a unit Reynolds number of about 6.9×107 m−1. The predicted boundary-layer and the wall static pressure distribution using SST k-ω model shows better agreement with the experimental data compared to the BSL model and hence indicates superior capability to capture the onset and the amount of flow separation due to SWBLIs. Moreover, the terminal shock structure at different operating modes as well as the “unstart because of SWBLIs” is predicted quite accurately using the model. The wall temperature condition is found to have a strong effect on the amount of flow separation at the cowl and the subsequent interactions. Further, the results show that the sidewalls have a marginal effect on the centerline wall static pressure, though a three-dimensional flowfield with two stream-wise vortices are observed close to it as a result of the swept SWBLIs of the cowl shock with the sidewall boundary-layer leading to a higher loss in performance.

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“…Both applications are highly relevant in the present Indian context [1][2][3][4][5] , as well as internationally. [6][7][8][9][10][11] These flows cover the entire range of physical phenomena outlined above, and their modelling in the CFD context is discussed in detail. They also bring out the CFD challenges involved in practical applications.…”

mentioning

confidence: 99%

Computational Fluid Dynamics in Hypersonic Aerothermodynamics

Sinha

2010

DSJ

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Hypersonic flows are characterised by high Mach number and high total enthalpy. An elevated temperature often results in thermo-chemical reactions in the gas, which play a major role in aerothermodynamic characterisation of high-speed aerospace vehicles. Hypersonic flows in propulsion components are usually turbulent, resulting in additional effects. Computational simulation of such flows, therefore, need to account for a range of physical phenomena. Further, the numerical challenges involved in resolving strong gradients and discontinuities add to the complexity of computational fluid dynamics (CFD) simulation. In this article, physical modelling and numerical methodology-related issues involved in hypersonic flow simulation are highlighted. State-of-the-art CFD challenges are discussed in the context of two prominent applicationsthe flow in a scramjet inlet and the flow field around a re-entry capsule.

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Three-dimensional viscous analysis of a Mach 5 inlet and comparison with experimental data

Cited by 14 publications

References 5 publications

Numerical Simulations of Flow in a 3-D Supersonic Intake at High Mach Numbers

Numerical Simulations of Flow in a 3-D Supersonic Intake at High Mach Numbers

Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Computational Fluid Dynamics in Hypersonic Aerothermodynamics

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