Abstract
In this study, we numerically examine thrust performance of the linear aerospike nozzle micro-thruster for various nozzle spike lengths and flow parameters in order to identify optimal geometry(s) and operating conditions. Decomposed hydrogen-peroxide is used as the monopropellant in the studies. Performance is characterized for different flow rates (Reynolds numbers) and aerospike lengths, and the impact of micro-scale viscous forces is assessed. It is found that 2-D full micro-aerospike efficiencies can exceed axisymmetric micro-nozzle efficiencies by as much as 10%; however, severe penalties are found to occur for truncated spikes at low Reynolds numbers.
Date of this Version
2007
DOI
10.2514/6.2007-3984
Recommended Citation
Zilic, A; Hitt, D L.; and Alexeenko, Alina A., "Numerical Simulations of Supersonic Flow in a Linear Aerospike Micronozzle" (2007). School of Aeronautics and Astronautics Faculty Publications. Paper 14.
http://dx.doi.org/10.2514/6.2007-3984
Comments
This is the published version of A. Zilic, D. Hitt, and A. Alexeenko. 2007. “Numerical Simulations of Supersonic Flow in a Linear Aerospike Micro Nozzle”. First published as an AIAA 37th AIAA Fluid Dynamics Conference and Exhibit Paper and is available online at: http://arc.aiaa.org/doi/pdf/10.2514/6.2007-3984.