Authors :
Vidhya. S
Volume/Issue :
Volume 8 - 2023, Issue 12 - December
Google Scholar :
http://tinyurl.com/bdhjvutd
Scribd :
http://tinyurl.com/y9ajtjjy
DOI :
https://doi.org/10.5281/zenodo.10389841
Abstract :
A Computational Fluid Dynamics Approach
to analyse the variations of standard missile geometry
with rectangular fin under varying angle of attacks with
different ranging Mach number in Supersonic ranges.
Here the complete study is focused in static stability
derivatives while using a Reynolds Navier stokes method
to compute the results. The projectile model used for the
study is the basic finned missile with a calibre of 0.03m.
The results obtained from the paper allow us to
understand the Mach number values ranging from
transonic regime to supersonic range.
Keywords :
Aerodynamic Coefficients, Static stability, Computational Approach.
A Computational Fluid Dynamics Approach
to analyse the variations of standard missile geometry
with rectangular fin under varying angle of attacks with
different ranging Mach number in Supersonic ranges.
Here the complete study is focused in static stability
derivatives while using a Reynolds Navier stokes method
to compute the results. The projectile model used for the
study is the basic finned missile with a calibre of 0.03m.
The results obtained from the paper allow us to
understand the Mach number values ranging from
transonic regime to supersonic range.
Keywords :
Aerodynamic Coefficients, Static stability, Computational Approach.
