Flow Simulation over a Bulbous Heat Shield of a Typical Launch Vehicle
Manoj R1, Ranjith Kumar A2, Gopalsamy Murugesan3, P. Jeyajothiraj4
1Mr. Manoj R, UG Scholar, Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore (Tamil Nadu), India.
2Mr. Ranjith Kumar A, 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: 2944-2948 | Volume-8 Issue-2S11 September 2019 | Retrieval Number: B13750982S1119/2019©BEIESP | DOI: 10.35940/ijrte.B1375.0982S1119
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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 Simulation of flow field over a sharp and blunt nose cone bulbous heat shield are carried out. Software used for the simulation is ANSYS 19.2 student version. The Simulations are carried out in the Mach no. range 0.8 to 1.2 (transonic regime). Simulation results are analyzed in detail. Besides, Shock Strength on the heat shield for all the simulation results are obtained. Based on the studies, bulbous heat shield which gives least shock strength is recommended for the payload fairing configuration.
Keywords: Sharp and Blunt Nose Cone, Bulbous Heat Shield, Numerical Simulation of Flow Field, Payload Fairing Configuration.
Scope of the Article: Heat Transfer