Compressible Flow

Use this for “What area ratio A/A∗ gives M = 2? What subsonic M has A/A∗ = 1.6875?”

Use this for “Air from a tank at 500 kPa and 500 K flows through a 0.001 m² throat at M = 1. Find ṁ.”

Use this for “Air at M₁ = 2 meets a wedge and the shock stands at β = 40°. Find θ, p₂/p₁ and M₂.”

Use this for “A pitot probe flies at M₁ = 2 where p₁ = 20 kPa. What does it read? What M₁ gives a reading of 112.8 kPa?”

Use this for “A nozzle with Aₑ/Aₜ = 1.6875 runs from 1000 kPa. What happens as the back pressure falls to 50 kPa?”

Use this for “A nozzle with pₑ = 40 kPa fires at sea level, where the air is at 101.3 kPa. Is it overexpanded?”

Use this for “A jet flies at M = 2. What is the half-angle μ of its Mach cone? What M gives μ = 45°?”

Use this for “Air at M₁ = 2 turns round a 10° convex corner. Find ν₁, ν₂ and M₂.”

Use this for “Air enters a 5 cm duct at M = 0.5 with f = 0.005. What is the Mach number 2 m downstream?”

Use this for “Air flows at M = 0.4 in a heated duct. Find p/p∗, T/T∗, T₀/T₀∗ and p₀/p₀∗ for Rayleigh flow.”

Use this for “Air at M = 0.3 and T₀ = 400 K takes in 300 kJ/kg in a duct. Find the exit Mach number and the heat that chokes it.”