Title: Computational Modeling and Comparative Analysis of Dual Bell Nozzle with Bell Nozzle
Authors: Mr.MD Khaleel & Niharanjan Hazarika
Organisation: MLR Institute of Technology and Management.
The concept of Altitude adaptive rocket nozzles recently received greater importance and interest in the space explorations and other such applications in space and rocket technology. In the recent progress of the combustion expansion system the rocket nozzles are greatly revised from both application and design perspectives. One of such development is the dual bell nozzle. Dual Bell Nozzle is an advanced rocket engine nozzle concept with an altitude- adapted capability. The main advantage of the Dual Bell Nozzle is to increase the efficiency of the nozzle. This nozzle concept is promising for application to existing and near term launch vehicle with a simple modification to current bell type nozzle configuration. The design and analysis of Dual Bell Nozzle and Bell Nozzle will be done in Catia, Hypermesh and Fluent software. The values of Mach number, pressure and temperature of Dual Bell Nozzle will be compared with Bell Nozzle.
Keywords: Bell Nozzle, Dual Bell Nozzle, Performance, Mach, Dynamic Pressure, Velocity
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