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An Efficient Power-On Base Pressure Prediction Inside the Tube Using Axisymmetric and Quasi-Steady Computation

An Efficient Power-On Base Pressure Prediction Inside the Tube Using Axisymmetric and... In this study, an efficient prediction technique is developed to investigate the power-on base pressure of a missile inside the tube during launch phase. Complex flow passage inside the tube is simplified using flow-path modeling. Base pressures on the missile inside the tube are predicted with axisymmetric and quasi-steady computations with a fully turbulent flow assumption. The computational results of base pressures for low and high thrust conditions agree well with measurement data of launch tests. Moreover, flow features related to the generation of the base pressure are demonstrated and discussed with the flow-field data for each thrust condition. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical & Space Sciences Springer Journals

An Efficient Power-On Base Pressure Prediction Inside the Tube Using Axisymmetric and Quasi-Steady Computation

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References (9)

Publisher
Springer Journals
Copyright
Copyright © 2019 by The Korean Society for Aeronautical & Space Sciences
Subject
Engineering; Aerospace Technology and Astronautics; Fluid- and Aerodynamics
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-019-00169-2
Publisher site
See Article on Publisher Site

Abstract

In this study, an efficient prediction technique is developed to investigate the power-on base pressure of a missile inside the tube during launch phase. Complex flow passage inside the tube is simplified using flow-path modeling. Base pressures on the missile inside the tube are predicted with axisymmetric and quasi-steady computations with a fully turbulent flow assumption. The computational results of base pressures for low and high thrust conditions agree well with measurement data of launch tests. Moreover, flow features related to the generation of the base pressure are demonstrated and discussed with the flow-field data for each thrust condition.

Journal

International Journal of Aeronautical & Space Sciences – Springer Journals

Published: May 9, 2019

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