Design of Minimum Length Supersonic Nozzle using the Method of Characteristics
Nirmith Kumar Mishra1, A Sai Kumar2, M Ganesh3, Mohd Abdul Rehman Alam4
1Nirmith Kumar Mishra, Department of Aeronautical Engineering, MLR Institute of Technology, Hyderabad, Telangana, India.
2A.Sai Kumar, Department of Aeronautical Engineering, MLR Institute of Technology, Hyderabad, Telangana, India.
3M.Ganesh, Department of Aeronautical Engineering, MLR Institute of Technology, Hyderabad, Telangana, India.
4Mohd Abdul Rehman Alam, Department of Aeronautical Engineering, MLR Institute of Technology, Hyderabad, Telangana, India.
Manuscript received on November 15, 2019. | Revised Manuscript received on 20 November, 2019. | Manuscript published on December 10, 2019. | PP: 1370-1374 | Volume-9 Issue-2, December 2019. | Retrieval Number: B6183129219/2019©BEIESP | DOI: 10.35940/ijitee.B6183.129219
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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: The work focuses upon design of minimum length supersonic nozzle, using the method of characteristics, for the given combustion chamber conditions, which are going to serve as nozzle inlet conditions. It is assumed that the flow has somehow been accelerated to the sonic value through a suitable convergent nozzle and from that point; the divergent portion of the nozzle is to be designed using the method of characteristics. The optimum exit area and hence, the Mach number are predicted and this Mach number is the value for which the nozzle has to be designed. The results obtained are validated with the results obtained by validation in ANSYS and based on the Observation, followed by a Discussion on the Optimisation of results.
Keywords: Method of Characteristics, Prandtl – Meyer Function, Expansion fans.
Scope of the Article: Digital System and Logic Design