(modified from anderson, question 1.1) consider the supersonic and hypersonic flow of air (with constant ratio of specific heats, y=1.4) over a 2-d wedge with a half-wedge angle of 20 degrees. let e denote the half-wedge angle and ß the shock wave angle. then ß - 0 is a measure of the shock layer thickness. a. make a plot of ß – 0 vs. the free-stream mach number m. from mo = 2 to 20. make some comments as to what mach number range results in a thin shock layer? b. plot the static pressure ratio, static temperature ratio, and the static density ratio across the shock for the same mach number interval considered in part a. c. would you expect to get a smaller or larger shock layer thickness if you have considered real gas effects (i. e., chemical reactions) for the mach number range you have determined in part (a) resulting a thin shock layer. explain your reasoning.