Using thin-airfoil theory, determine an airfoil camber line and design angle of attack that meet the following requirements: The lift coefficient is ce = 0.4 . There is no leading-edge suction peak . The airfoil has neutral static stability, SM = 0 . The camber line is a cubic function of x The chord line is on the x axis a) Determine the thin-airfoil theory constants B and B. b) Derive an equation for the camber line (include a plot), and find the design angle of attack. c) Verify your results using a NACA 0008 airfoil in mfoil: import your camber line, run at the design angle of attack, check the lift coefficient and center of pressure, and check for a suction peak (include the cp plot).