Numerical Simulation of Supersonic Jet Control by Tabs with Slanted Perforation
Author:
Affiliation:
1. Department of Aeronautical Engineering , Rajalakshmi Engineering college , Chennai , Tamil Nadu , India
2. Aerospace Engineering , Madras Institute of Technology, Anna University , Chennai , Tamil Nadu , India
Abstract
Publisher
Walter de Gruyter GmbH
Subject
Aerospace Engineering
Link
https://www.degruyter.com/document/doi/10.1515/tjj-2019-0015/pdf
Reference18 articles.
1. Bradbury LJ, Khadem AH. The distortion of a jet by tabs. J Fluid Mech. 1975;70:801–13.
2. Zaman KB, Reeder MF, Samimy M. Effect of tab geometry on the flow and noise field of an axisymmetric jet. Aiaa J. 1993;31:609–19.
3. Lovaraju P, Paparao KP, Rathakrishnan E. Shifted cross wire for supersonic jet control. AIAA Paper, 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2004;2004–4080. https://doi.org/10.2514/6.2004-4080.
4. Sreejith RB, Rathakrishnan E. Supersonic jet control with cross-wire. AIAA Paper, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 07 July 2002 – 10 July 2002 Indianapolis, Indiana. 2002;2002–4059. https://doi.org/10.2514/6.2002-4059.
5. Elangovan S, Rathakrishnan E. Studies on high speed jets from nozzles with internal grooves. Aeronaut J. 2004;108:43–50.
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