A glider's lift and drag coefficients are modeled as functions of the angle of attack $\\alpha$ (in radians) by $C_L = 5\\alpha$ and $C_D = 0.02 + 0.1\\alpha^2$. The glide ratio is defined as $\\frac{L}{D} = \\frac{C_L}{C_D}$. What angle of attack $\\alpha$ maximizes the glide ratio?