Manufacturing the Model of P3F Aircraft Half Wing and Experimental Study the Effects of Addition Winglet to it in Drag Reduction

In past years, efforts to reduce the effect of wing tip vortices and reduce drag on aircraft has attra cted many scientists of the world. One of the important activities carried out in this regard is installation of winglet at the wi ng tip. Nowadays, purpose of many researches is to achieve the best installation of winglet at different angle of attack. Some paramete rs such as speed or angle of attack, changes in different phases of flight. In t his study winglet with two angles of 30 and 60 degr ees mounted on P3F aircraft half wing model and its effects on the reduction of drag compared with wing without winglet. Tests has been conducted at Shiraz University of Technology Wind tunnel at three speed s 15 , 20 and 25 m/s , and with different angle of attacks namely: 0 , 3 and 7 degrees. The results of experiments show the drag f orce reduction due to using winglet with different cant angles. It is also shown that by changing flight conditions, to achieve a fa vorable situation, we need to change the winglet ca nt angle. Based on the results, the winglet with 60 degree cant angle, decreases dr ag about 8 %. and with 30 degree cant angle, decrea ses drag up to 4 %.