Numerical Investigation of Flow over a Canard Controlled Missile Configuration in Subsonic and Transonic Flow Regimes

International Journal of Mechanical Engineering
© 2018 by SSRG - IJME Journal
Volume 5 Issue 10
Year of Publication : 2018
Authors : Harish.M, Keerthi Varman.N, Muthu Kumar R. Kavin R, Renuga.R
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How to Cite?

Harish.M, Keerthi Varman.N, Muthu Kumar R. Kavin R, Renuga.R, "Numerical Investigation of Flow over a Canard Controlled Missile Configuration in Subsonic and Transonic Flow Regimes," SSRG International Journal of Mechanical Engineering, vol. 5,  no. 10, pp. 5-9, 2018. Crossref, https://doi.org/10.14445/23488360/IJME-V5I10P102

Abstract:

The transonic aerodynamics of a missile body is critical, which dictates the vehicle's structural design aspect and controllability. ANSYS-FLUENT has been used to investigate the aerodynamic characteristics over a Canard controlled missile configuration for subsonic and transonic Mach numbers ranging from 0.6 to 2. The co-efficient of pressure, shock location, flow separation and reattachment regions have been extracted.

Keywords:

Missiles, Canard, Fins, Transonic Aerodynamics

References:

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