Publication Date: 2023/12/15
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.
DOI: https://doi.org/10.5281/zenodo.10389841
PDF: https://ijirst.demo4.arinfotech.co/assets/upload/files/IJISRT23DEC582.pdf
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