The airplane has the drag polar of C = 0.02 + 0.06 C, CL=1.4 and wing span=1.8m. The sweep angle of quarter chord line is 15. The normal distance from wing center line to located at one-third of the semi . Gato centroid of wing panel area is per radian (where CL is angle) is span. The roll stability derivative, moment coefficient, is sideslip (round off to 2 decimal place).