Ramjet Inlet

Ramjet Inlet (propulsion/ramjet/ramjet-inlet)

Use when the task is supersonic ramjet inlet analysis: diffuser pressure recovery, exit total pressure, and the Kantrowitz starting verdict for an airbreathing hypersonic engine.

Domain quick reference

Units are SI throughout: pressures in Pa, Mach number and all ratios dimensionless, gamma = 1.4 for air:

• Diffuser total pressure recovery pi_d = pt2 / pt0, the ratio of the diffuser exit total pressure to the freestream total pressure.
• Isentropic recovery: pi_d = 1.0, the ideal lossless deceleration; the reference ceiling, unreachable at a supersonic Mach number.
• Normal shock recovery at the flight Mach number (pitot-type inlet, shock standing at the cowl lip), gamma = 1.4: pi_d = [6 M^2 / (M^2 + 5)]^3.5 * [6 / (7 M^2 - 1)]^2.5 with values 0.7209 at M = 2 and 0.3283 at M = 3.
• Freestream total pressure pt0 = p0 * (1 + 0.2 M0^2)^3.5; the exit total pressure is pt2 = pi_d * pt0.
• Kantrowitz starting criterion: the inlet with contraction ratio CR = Acapture / Athroat starts (swallows the lip shock) only when CR <= CR_K(M0), the quasi-steady choked-throat limit: CR_K(M) = (1 / M) * pi_d_ns(M) * (1 + 0.2 M^2)^3 * (1.2)^-3 with pi_d_ns(M) the normal shock recovery at M; CR_K rises from 1.0 at M = 1 toward about 1.666 as the Mach number grows.
• Starting limit Mach number: the M that solves CR_K(M) = CR for a fixed contraction ratio; a contraction above about 1.666 (gamma = 1.4) can never start at any Mach number.
• Ramjet inlet practice sits in the FAR-33 engine design context.

Workflow

1. Collect the flight Mach number, the freestream static pressure and temperature, and the inlet contraction ratio.
2. Compute the freestream total pressure and the normal shock recovery with normal_shock_total_pressure_ratio.
3. Compare against the isentropic limit with isentropic_pressure_recovery and select the model with pressure_recovery.
4. Compute the diffuser exit total pressure with exit_total_pressure.
5. Apply the starting criterion: kantrowitz_contraction_limit at the flight Mach number, or kantrowitz_limit_mach for a fixed contraction ratio, and judge with inlet_starts.
6. Gate the ramjet intake assessment on the recovery and the start verdict.

Pitfalls

• Using isentropic recovery at a supersonic Mach number: the ideal deceleration is the ceiling, the normal shock recovery at the flight Mach is the achievable value for a pitot-type inlet.
• Reading the starting criterion backwards: a higher contraction ratio is not easier to start, it needs a higher Mach number; above CR_K the inlet stays unstarted (buzz) until the flow starts.
• Confusing the Kantrowitz limit with the operating recovery: CR_K is a startability limit on the contraction ratio, not the diffuser total pressure ratio.
• Expecting a contraction above about 1.666 (gamma = 1.4) to start: no Mach number starts it, variable geometry or spillage is required.
• Using the normal shock model below M = 1: the normal shock relation is defined at supersonic Mach only, the isentropic branch is the subsonic limit.

Behavior contract (gate 3)

The recovery, exit total pressure, and Kantrowitz starting logic is exercised by the gate 3 contract test: scripts/test_ramjet_inlet.py against scripts/ramjet_inlet_logic.py (stdlib unittest, offline). Run: python3 scripts/test_ramjet_inlet.py

Compliance

• Standards referenced, not reproduced: FAR-33 is US government work (public domain); the normal shock relations, the isentropic diffuser recovery, and the Kantrowitz starting criterion are common propulsion and intake methodology, summary-only per standards-map.yaml.
• compliance: STANDARDS-REF, gated: false.