Volume 11, 2019Progress in Propulsion Physics – Volume 11
|Page(s)||517 - 528|
|Published online||08 February 2019|
Design of an arc-based thrust-optimized nozzle contour
School of Mechanical and Manufacturing Engineering UNSW Australia Sydney, NSW 2052, Australia
2 School of Engineering and Information Technology UNSW Canberra Canberra, ACT 2600, Australia
3 Aerospace Engineering Department California Polytechnic State University San Luis Obispo, CA 93407, USA
A total of ten arc-based nozzle contours have been numerically compared to an existing thrust-optimized design. Verification and validation of the numerical model was achieved using published experimental data and the resulting numerical uncertainty of the model relative to thrust was less than 0.10%. Analysis of the arc-based nozzles indicated that the contour angles had the greatest effect on thrust. Optimization of the contour angles suggested that an increase in thrust coefficient of 0.25% could be achieved compared to the existing thrust-optimized nozzle. The result shows that an arc-based design method may be used to produce an equivalent thrust-optimized nozzle.
© 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.