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Computational Fluid Dynamics Analysis of Advanced Rocket Nozzle


Author : Balaji Krushna .P , B.Balakrishna and P.SrinivasaRao

Pages : 448-452, DOI:http://Dx.Doi.Org/10.14741/Ijcet/Spl.2.2014.83
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Abstract

Special attention is then given to altitude-adaptive nozzle concepts, which have recently received new interest in the space industry. The reduction of Earth-to-orbit launch costs in conjunction with an increase in launcher reliability and operational efficiency are the key demands on future space transportation systems, like single-stage-to- orbit vehicles (SSTO). The realization of these vehicles strongly depends on the performance of the engines, which should deliver high performance with low system complexity Current research results are presented for dual-bell nozzles. The main part of the paper addresses dual-bell nozzle concepts with improvements in performance as compared to conventional nozzle achieved by altitude adaptation and, thus, by minimizing losses caused by over- or under expansion.The result shows the variation in the Mach number, pressure, temperature distribution and turbulence intensity.

Keywords: Altitude adaptation, Dual bell nozzle, Nozzle pressure ratio, Over-expansion factor.

Article published in International Conference on Advances in Mechanical Sciences 2014, Special Issue-2 (Feb 2014)

 

 

 

 

 

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