1. Consider a symmetrical airfoll with a trailing edge flap, placed in a uniform flow with velocity V... The flap covers the last quarter of the airfoil chord, so that the flap hinge is located at the three- quarter-chord, x = 0.75c. The flap deflection angle 8, which is defined positive for a downward deflection of the flap, and the angle of attack a are both assumed to be small. a. Make a sketch of the configuration and calculate the coefficients A0, A and A. b. Compute the lift coefficient of the airfoil as a function of a and 8, and determine the lift slope, dc//da, and the flap efficiency, dc/d8. Determine the position of the center of pressure for a = 0. Is it a function of the flap angle 8? I C. 1. Consider the two-dimensional situation where a vortex of strength To is located at a distance Ax behind the trailing edge of a cambered airfoil, as sketched in the figure below. The airfoil has a parabolic camber distribution z(x), according to: z(x) ) = kx (1-) where 0 x c; k is a parameter indicative of the amount of camber. Az a. b. V C. 4x Calculate the value of k, such that the maximum camber of the airfoil is 2.5% of the chord. Discuss how the vortex will affect the lift of the airfoil: will it increase, decrease or remain the same? Explain your answer! Determine the circulation I of the airfoil, with the effect of the downstream vortex included, using a discrete-vortex representation (i.e., the circulation of the airfoil is represented by a discrete vortex at % chord and with a control point at % chord). d. Compute the corresponding lift coefficient of the airfoil. To x