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.
TY - JOUR
AU - Al Kaabi, Hamad
AU - Petrović, Zlatko
AU - Đukanović, Gordana
PY - 2019
UR - https://omorika.sfb.bg.ac.rs/handle/123456789/996
AB - 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.
PB - Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek
T2 - Tehnički vjesnik
T1 - Numerical and Experimental Determination of Canard Controlled Missile Aerodynamic Coefficients in Subsonic Regime
EP - 680
IS - 3
SP - 674
VL - 26
UR - conv_2342
ER -
@article{
author = "Al Kaabi, Hamad and Petrović, Zlatko and Đukanović, Gordana",
year = "2019",
abstract = "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.",
publisher = "Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek",
journal = "Tehnički vjesnik",
title = "Numerical and Experimental Determination of Canard Controlled Missile Aerodynamic Coefficients in Subsonic Regime",
pages = "680-674",
number = "3",
volume = "26",
url = "conv_2342"
}
Al Kaabi, H., Petrović, Z.,& Đukanović, G.. (2019). Numerical and Experimental Determination of Canard Controlled Missile Aerodynamic Coefficients in Subsonic Regime. in Tehnički vjesnik
Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek., 26(3), 674-680.
conv_2342
Al Kaabi H, Petrović Z, Đukanović G. Numerical and Experimental Determination of Canard Controlled Missile Aerodynamic Coefficients in Subsonic Regime. in Tehnički vjesnik. 2019;26(3):674-680.
conv_2342 .
Al Kaabi, Hamad, Petrović, Zlatko, Đukanović, Gordana, "Numerical and Experimental Determination of Canard Controlled Missile Aerodynamic Coefficients in Subsonic Regime" in Tehnički vjesnik, 26, no. 3 (2019):674-680,
conv_2342 .
