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Numerical exploration of starting process in supersonic nozzle

Published online by Cambridge University Press:  03 February 2016

S. Saha  and
D. Chakraborty
S. Saha
Affiliation:
Computational Combustion Dynamics Division, Defence Research and Development Laboratory, Hyderabad, India
D. Chakraborty
Affiliation:
Computational Combustion Dynamics Division, Defence Research and Development Laboratory, Hyderabad, India
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Abstract

The starting process in a supersonic nozzle is numerically simulated. The Navier Stokes equations, in axisymmetric form, are solved using a higher order spatial and temporal accurate scheme. Good comparisons between experimental and numerical values of various flow parameters form the basis of further analysis. The insight of the starting process in the nozzle, namely, the movement of primary and secondary shocks and contact discontinuity, has been obtained through analysis of various flow parameters. It has been observed that the inviscid phenomenon is more predominant in the flow development process. Parametric studies have been carried out to determine the effect of nozzle divergence angle on the starting process.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1115 , January 2007 , pp. 51 - 58
Copyright
Copyright © Royal Aeronautical Society 2007 

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