Flow Analysis of Hybrid Rocket Nozzle Exhaust and Its Effects on Launch Pad and Guide Stand
Tejas Christopher1, Prajwal Ashok Kumar2, Siddalingappa P K3, N K S Rajan4
1Tejas Christopher, Department of Aeronautical Engineering, Nitte Meenakshi Institute of Technology, Bangalore, India.
2Prajwal Ashok Kumar, Department of Aeronautical Engineering, Nitte Meenakshi Institute of Technology, Bangalore, India.
3Siddalingappa P K, Department of Aeronautical Engineering, Nitte Meenakshi Institute of Technology, Bangalore, India.
4N K S Rajan, CGP Laboratory, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India.
Manuscript received on 02 August 2019. | Revised Manuscript received on 07 August 2019. | Manuscript published on 30 September 2019. | PP: 7453-7459 | Volume-8 Issue-3 September 2019 | Retrieval Number: C5538098319/2019©BEIESP | DOI: 10.35940/ijrte.C5538.098319
Open Access | Ethics and Policies | Cite | Mendeley | Indexing and Abstracting
© 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: The exhaust from the nozzle will be at very high temperature and the high temperature exhausts effect the launch pad and guide stand. In this research, the computational analysis is done on Hybrid Rocket Nozzle Exhaust and Its Effects on Launch Pad and Guide Stand. The flow characteristics such as pressure, temperature, velocity and Mach number at different time period have been studied for various exit geometries using ANSYS Fluent solver. Exhaust speeds vary, depending on the expansion proportion of the nozzle. The rocket nozzle along with guide stand is modelled. The aeroacoustics effects from the nozzle on Launch Pad and Guide Stand have been studied separately using acoustics model.
Keywords: Hybrid Rocket, Nozzle, Supersonic Jet, Expansion, Computational Fluid Dynamics
Scope of the Article: Analysis of Algorithms and Computational Complexity