Numerical simulations of the flow through the inlet and isolator of a Mach 4 dual mode scramjet

Janarthanam, S.; Babu, V.

doi:10.1017/s0001924000007302

Cited by 13 publications

(2 citation statements)

References 7 publications

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“…Additionally unstart due to back pressure created by the combustor has been noticed to be depending upon inlet geometry, contraction ratio and isolator length. Later Janarthanam and Babu (2012) have performed computational study employing Emami's intake geometry and experimental conditions. Three different cowl lengths and five cowl convergence angles were re-investigated computationally.…”

Section: Introductionmentioning

confidence: 99%

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

John

Senthilkumar

2018

JAFM

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This paper discusses the performance enhancement of supersonic air intake model through the implementation of blunted leading edge to the cowl lip section of the model. A supersonic air intake model with sharp cowl leading edge is initially considered to numerically investigate its performance. Mach 3, supersonic intake flow through the base model has been simulated using commercial CFD package Ansys Fluent-15. Comparison of numerical predictions and experimental measurements is presented to demonstrate the correctness and accuracy of numerical frame work followed in the present study. Higher order spatial accuracy of the solver along with suitably refined mesh helped in accurate capturing of the flow field. Modification to the cowl lip is proposed as an effective method to improve the performance of the supersonic air intake. Two different blunted cowl leading edge geometries were investigated to identify the possible enhancement in performance parameters. Improvement in mass capture and combustion stability attained through the use of forward shifted blunt cowl leading edge is presented. It is also revealed through the present study that the blunt cowl leading edge can reduce the intensity of shock wave boundary layer interaction occurring at the isolator entry section. Deviation in total pressure recovery and flow distortion observed with different supersonic air intake models are also discussed with reasons for the same. This study demonstrates the scope of overall improvement in scramjet engine performance through the use of suitably positioned blunt cowl leading edge.

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Section: Introductionmentioning

confidence: 99%

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

John

Senthilkumar

2018

JAFM

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“…Azam Che Idris et al, Suggested Y+ values less than 1 to simulate shock wave boundary layer interactions in hypersonic intake [4]. Senthil kumar et al, have performed CFD simulations on SCRAMJET Inlet and noticed the direct effect of loss in total pressure recovery, inlet unsteadiness and flow distortion due to increase in cowl angle [5]. Janarthanam et al, CFD results of three-dimensional flow in the dual mode scramjet intake-isolator are agreed with experimental results at Mach 4 using SST k-ω turbulence model [6].…”

Section: Literature Reviewmentioning

confidence: 99%

Grid Adaptive Technique for Simulation of Scramjet Intake-Isolator at Hypersonic Speeds

Sandeep

Gupta²

2023

ARFMTS

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Hypersonic intake is one of the major components of Scramjet engine. It compresses the incoming hypersonic flow through a series of oblique shocks as the flow passes through intake-isolator section before entering the combustion chamber, which is essential for efficient combustion. The shocks generated inside in the intake interacts with boundary layer following shock boundary layer interaction and flow separation. The separated flow blocks the flow capture area such that engine expresses unstarting phenomenon. Understanding and mitigating such flow phenomenon is a challenging task. With respect to hypersonic speeds the experimental facilities are very limited. The only alternative to solve this problem is Computational Fluid Dynamics because of its capabilities. But validation of CFD results with analytical or experimental is the foremost prerequisite to chase computational analysis. Mostly at high speeds the precision of CFD results rest on the type of grid, number of elements and turbulence model used. So, in this paper, computational analysis of hypersonic intake is carried out through designed conditions to ensure the correct CFD process is used by varying number of elements in fluid domain by grid adaptive technique using ANSYS Fluent and satisfying Y+ parameter. The domain is analysed with various turbulence models and among them SST has predicted all the flow characteristics of scramjet intake-isolator at hypersonic speeds like separation bubble, shock reattachment, cowl shock etc similar to experimental results with the help of grid adaptive technique. So, grid adaptive technique is also proposed for simulation of scramjet intake at off-design conditions.

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Numerical Investigation on Shock-Wave and Boundary-Layer Interactions Inside the Axisymmetric and Planar Scramjet Intakes with Different Cowl Orientations

Sharath,

Jana

2024

Lecture Notes in Mechanical Engineering

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Numerical simulations of the flow through the inlet and isolator of a Mach 4 dual mode scramjet

Cited by 13 publications

References 7 publications

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

Grid Adaptive Technique for Simulation of Scramjet Intake-Isolator at Hypersonic Speeds

Numerical Investigation on Shock-Wave and Boundary-Layer Interactions Inside the Axisymmetric and Planar Scramjet Intakes with Different Cowl Orientations

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