An article in the Journal of Aircraft (1988) describes the computation of drag coefficients for the NASA 0012 airfoil. Different computational algorithms were used atM8 = 0.7 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, 96, 70, 83, 81, 85, 82, 80, and 84.
Compute the sample mean, sample variance, and sample standard deviation.