Author(s): Md Akhtar Khan, Sanjay Kumar Sardiwal, M.V.Sai Sharath, D.Harika Chowdary
Published in: International Journal of Engineering Research & Technology
License: This work is licensed under a Creative Commons Attribution 4.0 International License.
Volume/Issue: Vol.2 - Issue 11 (November - 2013)
Abstract - In this paper, a method based on the theory of characteristics is presented for two-dimensional, supersonic nozzle design. Minimum length of the supersonic nozzle has been calculated for the optimum Mach number at the nozzle exit with uniform flow at the diverging section of the nozzle by developing a MATLAB program. Numerical solution is established for the two dimensional, steady, in viscid, irrotational and supersonic flow. It is rational to assume the flow holds the consistency in the converging section and, thereby, an arbitrary shape is assumed for the converging section of the supersonic nozzle. The design considerations are concentrated at the diverging section.
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