Volume 11, 2019Progress in Propulsion Physics – Volume 11
|Page(s)||713 - 728|
|Published online||08 February 2019|
Experimental investigation of the effect of the air inlet angle and the combustion pressure in a ducted rocket combustor
Department of Aerospace Engineering, Politecnico di Milano Milan 20156, Italy
2 Faculty of Aerospace Engineering Technion — Israel Institute of Technology Technion City, Haifa 32000, Israel
The scope of the study is to evaluate the combustion efficiency of a ducted rocket combustor operating at different conditions, using a connected-pipe testing setup. An experimental parametric investigation was conducted to evaluate the effect of the inlet air-injection angles and the effect of the combustion pressure for different fuel-to-air ratios. The experimental results indicate that best energetic performance was obtained for an injection angle of 120°, i. e., against the main flow direction. The reason is that this way better mixing was obtained and the residence time increased. Characteristic velocity was found to decrease with decreasing the combustion pressure.
© The Authors, published by EDP Sciences, 2019
This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.