An experimental study was conducted on a subsonic wind tunnel to obtain aerodynamic coefficients for various situations in order to control the direction of a projectile. The angle of attack on the projectile was varied from $-5^{circ}$ to $15^{circ}$ and the roll angle of canard was changed from $0^{circ}$ to $90^{circ}$. The angle of attack on the canard was adjusted from $-20^{circ}$ to $20^{circ}$ and various inlet velocities were applied. Maximum Reynolds number based on the diameter of projectile was $5.5{ imes}10^5$. The measured aerodynamic coefficients showed the same results for the various inlet velocities, and the highest effect on the canard was shown when the canard was set to the roll angle of $0^{circ}$.