Chapter 8, Problem 8.6P

Consider the isentropic flow over an airfoil. The freestream conditions correspond to a standard altitude of 10.000 ft and $M_{\infty }=0.\text{82}$. At a given point on the airfoil, $M=\text{1 }.0$. Calculate p and T at this point. (Note: You will have to use the standard atmosphere table in Appendix E for this problem.)