Tehnički Vjesnik (Jan 2019)

Numerical and Experimental Determination of Canard Controlled Missile Aerodynamic Coefficients in Subsonic Regime

  • Hamad Al Kaabi,
  • Zlatko Petrović,
  • Gordana Djukanović

DOI
https://doi.org/10.17559/TV-20180724143418
Journal volume & issue
Vol. 26, no. 3
pp. 674 – 680

Abstract

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This paper discusses the computational and experimental approach to the determination of aerodynamic coefficients of canard controlled missile with wrap around tail fin. The paper presents results of subsonic flow at Mach 0.4. Angle of attack of the missile is varied from −10 to +10 degrees with an increment of 2 degrees. Canard deflection in the pitch plane is also varied at 0, 10, and 15 degrees. The results of the simulation are compared with the experimental data obtained by the wind tunnel measurements. Measured results confirm applicability of Spalart Allmaras turbulence model with adapted computational mesh to the determination of aerodynamic coefficients for canard controlled missiles.

Keywords