Rolling And Yawing Aerodynamic Performance Of An Aircraft Model

Lim, Swee Meng (2009) Rolling And Yawing Aerodynamic Performance Of An Aircraft Model. Project Report. UTeM, Melaka, Malaysia. (Submitted)

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Abstract

The present investigation primarily studies the effect of control surfaces on the coefficient of side force, CY, yawing moment, Cn, and rolling moment, Cl, of an airplane model using a close-loop subsonic wind tunnel. Effect of variation for the sideslip angle, angle of rudder and angle of ailerons will be tested in the wind tunnel in order to get the coefficient of side force, CY, yawing moment, Cn, and rolling moment, Cl. As expected, the rudder deflection is effective in controlling the yaw moment coefficient. The rudder deflection is inversely proportional to the yawing moment coefficient where as the rudder deflection increases the yawing moment coefficient will decreases. From the results the effective angle of rudder deflection is from -5º till -10º in controlling the yawing moment coefficient. Besides, from the results the ailerons deflection is effective in controlling the rolling moment coefficient and yawing moment coefficient. The direct effect of ailerons deflection is on the rolling moment coefficient. The ailerons deflection is directly proportional to the rolling moment coefficient where as the angle of ailerons deflection increases the rolling moment coefficient will increase. From the results the effective angle of ailerons deflection is from -5º till -15º in controlling the rolling moment coefficient.

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