shock-tubelisted

Use when you must determine the four-region state of a shock-tube run from the driver-to-driven diaphragm pressure ratio and driver sound-speed ratio: recover the incident-shock Mach number by deterministic bisection of the implicit diaphragm-match equation, then the post-shock pressure, temperature and density ratios with the region-2 absolute state, the contact-surface velocity shared by shocked driven gas and expanded driver gas with the region-2 and region-3 flow Mach numbers, the driver expansion wave ratios with the region-3 absolute state, and the fan head and tail wave speeds. Produces the incident-shock Mach number, the four-region state table and the contact checks that gate shock-tube facility design, driver-gas selection and gas-dynamics coursework. Trigger: shock tube, shock-tube run, diaphragm pressure ratio, contact surface, driver gas, driven gas, incident shock, driver sound-speed ratio, post-shock state, fan head wave, fan tail wave, four-region state table.
ashfordeOU/aero-agent-skills · ★ 0 · AI & Automation · score 78

Install: claude install-skill ashfordeOU/aero-agent-skills

# Shock-Tube Wave System (aerodynamics/high-speed/shock-tube) Use when the task is the classical one-dimensional shock-tube problem: a high-pressure driver gas (region 4) separated by a diaphragm from a low-pressure driven gas (region 1), both initially at rest, with the diaphragm burst releasing an incident shock into the driven gas, a contact surface between the two gases, and a centered expansion wave running back into the driver gas. This leaf recovers the incident-shock Mach number from the diaphragm pressure state alone, then resolves the four-region state. It pairs with normal-shock for the stationary-shock ratio context at a given upstream Mach number and with prandtl-meyer for the steady turning-fan context; the moving-shock, contact-surface and unsteady-wave content here has no other home in the high-speed pack. Pure stdlib, deterministic, offline. ## Domain quick reference - Incident shock into gas at rest at shock Mach Ms: p2/p1 = 1 + 2 gamma1 (Ms^2 - 1) / (gamma1 + 1), rho2/rho1 = (gamma1 + 1) Ms^2 / (2 + (gamma1 - 1) Ms^2), T2/T1 = (p2/p1) / (rho2/rho1); the shock speed is Ws = Ms a1 with a1 = sqrt(gamma1 R t1). - Induced flow behind the shock (contact-surface velocity): u2 = 2 a1 (Ms - 1/Ms) / (gamma1 + 1). The shock-frame downstream Mach number Mn2 = sqrt((1 + (gamma1 - 1) Ms^2 / 2) / (gamma1 Ms^2 - (gamma1 - 1) / 2)) stays below one; u2 = Ms a1 - Mn2 a2 links the frames. - Unsteady centered expansion into the driver gas: p3/p4 = (1 - (gamma