An article in the Journal of Aircraft (1988) describes the computation of drag coefficients for the NASA 0012 airfoil. Different computational algorithms were used at with the following results (drag coefficients are in units of drag counts; that is, one count is equivalent to a drag coefficient of 0.0001): 79, 100, 74, 83, 81, 85, 82, 80, and 84. Compute the sample mean, sample variance, and sample standard deviation, and construct a dot diagram.