Abstract
The scramjet engine plays a promising role for a successful future hypersonic flight system. The performance of scramjet system depends on many factors like mixing rate of fuel and air, proper flame stabilization mechanism and suitable injection system. The flame stabilization is provided by means of introducing a Cavity along the wall of the combustor. The cavity effects on the performance of supersonic combustion will be studied here with the help of three-dimensional combustor CFD model. The reliability of the numerical results obtained by using the computational approach depends on the proper validation of the CFD code with their corresponding experimental results. The corresponding experimental results from the literature will be identified and used here for the validation of the numerical code. The final CFD results after its validation with the experimental results will be presented in terms of x-y plots and contours for the discussion.
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This article (and all articles in the proceedings volume relating to the same conference) has been retracted by IOP Publishing following an extensive investigation in line with the COPE guidelines. This investigation has uncovered evidence of systematic manipulation of the publication process and considerable citation manipulation.
IOP Publishing respectfully requests that readers consider all work within this volume potentially unreliable, as the volume has not been through a credible peer review process.
IOP Publishing regrets that our usual quality checks did not identify these issues before publication, and have since put additional measures in place to try to prevent these issues from reoccurring. IOP Publishing wishes to credit anonymous whistleblowers and the Problematic Paper Screener [1] for bringing some of the above issues to our attention, prompting us to investigate further.
[1] Cabanac G, Labbé C and Magazinov A 2021 arXiv:2107.06751v1
Retraction published: 23 February 2022