Theoretical and Experimental of Evaluation of Flow Field Over a Double Delta Wing at Supersonic Speeds
Pavan Jacob Abraham1, Ashish John Kalathil2, Gopalsamy Murugesan3, P. Name Jeyajothiraj4
1Mr. Pavan Jacob Abraham A, UG Scholar, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
2Mr. Pavan Jacob Abraham, UG Scholar, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
3Mr. Gopalsamy Murugesan, Research Scholar, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
4Dr. P. Jeyajothiraj, Professor, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
Manuscript received on 17 October 2019 | Revised Manuscript received on 25 October 2019 | Manuscript Published on 02 November 2019 | PP: 2939-2943 | Volume-8 Issue-2S11 September 2019 | Retrieval Number: B13740982S1119/2019©BEIESP | DOI: 10.35940/ijrte.B1374.0982S1119
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: Numerical and experimental investigations of flow over double delta wing at supersonic speed are investigated. For numerical simulations, the body geometry is generated using SolidWorks software, mesh is created using Gambit and solution is obtained using Fluent software. For the experimental studies, stainless steel model is fabricated and tested in the supersonic wind turnel at mach 2.5 at 0 and 50 angle of attack. The results are presented in the present paper.
Keywords: Double Delta Wing, Supersonic Speed, Re-entry Launch Vehicle, Vortex Shedding.
Scope of the Article: Theoretical and Applied Fracture Mechanics