Aerodynamic Design of Rocket Launchers To Reduce Drag

Aerodynamic Design of Rocket Launchers To Reduce Drag
Authors : Er. Amandeep Singh Bhui
Publication Date: 28-12-2012


Author(s):  Er. Amandeep Singh Bhui

Published in:   International Journal of Engineering Research & Technology

License:  This work is licensed under a Creative Commons Attribution 4.0 International License.

Website: www.ijert.org

Volume/Issue:   Vol.1 - Issue 10 (December - 2012)

e-ISSN:   2278-0181


The main aim of this work was to modify and then investigate the effect of the modified Rocket Launcher”Ēs design on the Drag force produced due to it, so as to get an optimal design that finally leads to reduction of drag. To achieve the desired goal we tested the effect for the Hemi-spherical nose shape as compared to the Blunt shaped conventional Rocket Launcher. We used FLUENT as the CFD software for getting the drag values for the different nose shapes at different operating conditions. M261, Hydra-70 Light Weight Launcher, reusable, 19-tube, electrically fired 2.75-inch folding fin aircraft rocket (FFAR) launcher, was used as the basis for our investigation. While calculating the Coefficient of Parasite Drag in the forward flight, during Preliminary Helicopter Design process, it is a general practice that while calculating Coefficient of Parasite Drag for external loads, and additional 15% is added to the usual value of Coefficient of Parasite Drag for external loads. Now if somehow this 15% value be reduced, this will lead to reduction of drag. This Thesis work is one step in this direction.


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