An ideal turbojet engine is at altitude of 50,000 ft on a standard day with flight Mach number of 2.5. We are given the following design information: π = 18, Tt₄ = 3,000 °R, Cₚ = 0.24 Btu/lbm-ᵒ R, γ = 1.4, Hₚᵣ = 18,800 Btu/lbm.
a) Using the altitude tables, calculate T₀, and then find τ, a₀, τᵣ, τλ, and f