Development and Assessment of a Backward Facing Steps Planar Rocket Nozzle
- Corresponding Author:
- Shaaban Abdallah
Department of Aerospace Engineering
University of Cincinnati, OH 45221, USA
E-mail: [email protected]
Received date: April 10, 2014; Accepted date: June 06, 2014; Published date: June 16, 2014
Citation: Mandour, Shaaban Abdallah (2014) Development and Assessment of a Backward Facing Steps Planar Rocket Nozzle . Glob J Tech Opt 5:160. doi:10.4172/2229-8711.1000160
Copyright: © 2014 Mandour et al, This is an open-access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.
Large Rocket engine nozzles performance deteriorate because of asymmetric flow separation that lead to side loads. The dual-bell nozzle is a promising two operating modes nozzle which consists of a base nozzle with low area ratio and a nozzle extension with high area ratio. Although the dual-bell nozzle improves the performance of large rocket engines, it suffers from side loads that occur during the transition between the two operating modes. This paper presents and assess a new nozzle that consist of backward facing steps to minimize/eliminate side loads. The backward facing steps geometry guarantees fixed stable local separation at the steps edges at all altitudes, thus eliminates the possibility of side loads as the rocket ascends. The assessment of the nozzle performance is carried out using CFD simulation of turbulent Navier-Stokes equations solver (fluent 14.5). The computed results for both dual-bell and backward facing steps nozzles are compared with the dual-bell nozzle experimental data.