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|
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 5.10 (2018): 5-9.
Harish.M, Keerthi Varman.N, Muthu Kumar R. Kavin R, Renuga.R,(2018). Numerical Investigation of Flow over a Canard Controlled Missile Configuration in Subsonic and Transonic Flow Regimes. SSRG International Journal of Mechanical Engineering 5(10), 5-9.
The transonic aerodynamics of a missile body is critical, which dictates the structural design aspect and controllability of the vehicle. 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.
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Missiles, Canard, Fins, Transonic Aerodynamics