As a first step towards analyzing oblique shock waves in hypersonic flow, consider the limiting case of infinite Mach number. For this condition, do the following:
(a) Derive a relation between the deflection angle, θ and the oblique shock angle, β. Please submit an analytical derivation (something you have completed by hand), and explain the steps you are taking. You can then use a software package to check your answer if you'd like.
(b) Determine the maximum deflection angle (in degrees) obtained for flow of a monatomic gas, such as Argon, for which the specific heat ratio is 1.67. You may do this problem by theoretical analysis or by trial-and-error. Then, compute the maximum deflection angle (in degrees) for cold air (θ=1.40). Compare the two values.