Leading - Edge and Trailing - Edge Flaps In this problem, we study the aerodynamic impact of leading and trailing edge flaps on an airfoil. For this, we consider the camberline illustrated in the figure below. 0 obrace ( ) = 0 . 1 cobrace ( ) = 0 . 9 1 The leading and trailing edge flap deflection angles ( defined positively downwards ) are 0 and 1 , respectively, and both flaps have a length of 0 . 1 where is the airfoil length. In the following, assume small angles throughout and use Thin Airfoil Theory