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Research Article | Open Access
Volume 5 | Issue 10 | Year 2018 | Article Id. IJME-V5I10P102 | DOI : https://doi.org/10.14445/23488360/IJME-V5I10P102

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

Harish.M, Keerthi Varman.N, Muthu Kumar R. Kavin R, Renuga.R

Citation :

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," 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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