Incompressible & Compressible Aerodynamics

(A) 0 ) , 0 (t w (B) 0 ) , (2 2   t Lx w (C) 0 ) , 0 (2 2   tx w (D) 0 ) , (3 3   t Lx w Common Data for Questions 50 and 51: Consider an inviscid, adiabatic flow of air at free stream Mach Number, M ∞ = 2, across a compression corner (θ = 20°) as shown. The free stream total enthalpy is h 0∞ = 810 kJ kg-1. Assume that air is calorically perfect with γ = 1.4, R = 287 J kg-1 K-1. The shock angle β is