Izvorni znanstveni članak

https://doi.org/10.17559/TV-20180724143418

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

Hamad Al Kaabi ; University of Belgrade, Faculty of Mechanical Engineering Belgrade, Kraljice Marije 16, 11120, Belgrade 35, Serbia
Zlatko Petrović ; University of Belgrade, Faculty of Mechanical Engineering Belgrade, Kraljice Marije 16, 11120, Belgrade 35, Serbia
Gordana Djukanović ; University of Belgrade, Faculty of Forestry Belgrade, Kneza Viseslava 1, 11030 Belgrade, Serbia

Sažetak

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.

Ključne riječi

aerodynamic coefficients; canard; experimental method; numerical solution; missile; subsonic flow

Hrčak ID:

220991

URI

https://hrcak.srce.hr/220991

Datum izdavanja:

12.6.2019.

Posjeta: 2.816 *