Set by the Mach number

• A choke that belongs to two streams — A₃/Aₜ = 60, suction at 0.01 of the motive pressure; one-dimensional compressible duct; steam, γ = 1.3; 10 °C suction, 130 °C motive; ideal parts · ejector-map
• A compression that costs nothing in the end — Mach 3, twelve degrees total, gamma = 1.4 · compressible-exact · hero
• A compression that costs nothing in the end — Mach 3, gamma = 1.4 · compressible-exact
• A compression that costs nothing in the end — a normal shock in air, gamma = 1.4, at Mach numbers just above one · compressible-exact
• A compression that costs nothing in the end — Mach 3, twelve degrees total, gamma = 1.4 · compressible-exact
• A compression that costs nothing in the end — Mach 3, twelve degrees total · compressible-exact
• A compression that costs nothing in the end — Mach 3 turning through 12 degrees over a unit wall · compressible-exact
• A compression that costs nothing in the end — Mach 3, turns of 4 to 16 degrees over a wall of unit length · compressible-exact
• A compression that costs nothing in the end — air at gamma = 1.4, Mach 3 unless stated · compressible-exact
• A duct that cannot be run backwards — air, constant area, adiabatic, inlet Mach 0.3 · what-a-gas-carries-forward
• A duct that cannot be run backwards — air, constant area, adiabatic, inlet Mach 0.3 · what-a-gas-carries-forward
• A duct that cannot be run backwards — air, constant area, adiabatic · what-a-gas-carries-forward
• A duct that cannot be run backwards — air, constant area, adiabatic, inlet Mach 0.3 · what-a-gas-carries-forward
• A duct that cannot be run backwards — air, constant area, adiabatic, inlet Mach 0.3 · what-a-gas-carries-forward
• A gas that has not decided to react yet — Mach 5 in air at 300 K · what-a-gas-carries-forward · hero
• A gas that has not decided to react yet — Mach 5 in air at 300 K · what-a-gas-carries-forward
• A gas that has not decided to react yet — Mach 5 base, air at 300 K · what-a-gas-carries-forward
• A gas that has not decided to react yet — Mach 5 in air at 300 K, activation temperature 15,000 K · what-a-gas-carries-forward
• A gas that has not finished being shocked — Mach 6 in air at 300 K, vibrational temperature 3390 K · what-a-gas-carries-forward · hero
• A gas that has not finished being shocked — Mach 6 in air at 300 K, vibrational temperature 3390 K · what-a-gas-carries-forward
• A gas that has not finished being shocked — Mach 6 in air at 300 K · what-a-gas-carries-forward
• A shock that lies on the body — γ = 1.4, perfect gas — every limit here moves if γ does · hot-gas
• A shock that lies on the body — M∞ = 12 throughout — only the gas changes · hot-gas
• A shock that lies on the body — M∞ = 20 throughout — only the gas changes · hot-gas
• An instrument that takes a derivative — any Mach number — an instrument model, with no flow solved anywhere · optical-response · hero
• An instrument that takes a derivative — any Mach number — an instrument model, with no flow solved anywhere · optical-response
• An instrument that takes a derivative — any Mach number — the responses contain no velocity at all · optical-response
• An instrument that takes a derivative — any Mach number — an instrument model, with the shock's thickness prescribed · optical-response
• An instrument that takes a derivative — any Mach number — an instrument model, with no flow solved anywhere · optical-response
• An instrument that takes a derivative — any Mach number — an instrument model, with no flow solved anywhere · optical-response
• Friction moves the sonic point past the throat — exit area ratio 2.5, γ = 1.4 · nozzle-duct
• Friction moves the sonic point past the throat — exit area ratio 2.5, γ = 1.4 · nozzle-duct
• Friction moves the sonic point past the throat — exit area ratio 2.5, γ = 1.4 · nozzle-duct
• One view is enough, and the axis pays for it — any Mach number, a flow of revolution — noise relative to each instrument's own peak · optical-response · hero
• One view is enough, and the axis pays for it — any Mach number — an instrument model on a flow of revolution, the field prescribed · optical-response
• One view is enough, and the axis pays for it — any Mach number — a geometric construction on any axisymmetric field · optical-response
• One view is enough, and the axis pays for it — any Mach number, a flow of revolution — noise relative to each instrument's own peak · optical-response
• One view is enough, and the axis pays for it — any Mach number, a flow of revolution — independent noise on each ray · optical-response
• One view is enough, and the axis pays for it — any Mach number, a flow of revolution — noise relative to each instrument's own peak · optical-response
• Pressure has no speed — any Reynolds number — the abscissa is the Mach number and nothing else enters · pressure-poisson
• Pressure has no speed — Ma up to 2.00 — cone angle measured off the circles · sound-signal
• Pressure has no speed — any Reynolds number — the abscissa is the Mach number and nothing else enters · pressure-poisson
• Slower than either of them — air and water at atmospheric pressure — the speed of sound in a mixture · structure-and-mixture · hero
• Slower than either of them — air in water — the speed of sound in a mixture · structure-and-mixture
• Slower than either of them — air in water — the speed of sound in a mixture · structure-and-mixture
• Slower than either of them — at the void fraction that minimises each — the speed of sound in a mixture · structure-and-mixture
• Slower than either of them — air in water — the speed of sound in a mixture · structure-and-mixture
• Slower than either of them — air in water at one atmosphere — the speed of sound in a mixture · structure-and-mixture
• Slower than either of them — air in water — the speed of sound in a mixture · structure-and-mixture
• Slower than either of them — a velocity change of 2 m/s — the speed of sound in a mixture · structure-and-mixture
• Slower than either of them — air bubbles in water at one atmosphere — the speed of sound in a mixture · structure-and-mixture
• Slower than either of them — one per cent air in water, millimetre bubbles — the speed of sound in a mixture · structure-and-mixture
• The discontinuity that has a thickness — sea level, Pr = 3/4 — the model is outside its range above Mach three · nonlinear-wave
• The discontinuity that has a thickness — the first two rows hold at any Mach number; the last two do not · nonlinear-wave
• The discontinuity that has a thickness — Pr = 3/4, air at sea level — the third panel is outside the model's range · nonlinear-wave
• The equation that changes type inside its own answer — M∞ = 0.85, γ = 1.4 — the pressure distribution is a shape, not a solution · hot-gas · hero
• The equation that changes type inside its own answer — M∞ = 0.85, γ = 1.4 — the pressure distribution is a shape, not a solution · hot-gas
• The equation that changes type inside its own answer — M∞ = 0.85, γ = 1.4 — the shape is not a solution and says so · hot-gas
• The equation that changes type inside its own answer — M∞ = 0.9, γ = 1.4 — the shape is not a solution and says so · hot-gas
• The equation that changes type inside its own answer — C_p,min = −2τ — a thin-aerofoil peak suction, γ = 1.4 · hot-gas
• The equation that changes type inside its own answer — C_p,min = −2τ — a thin-aerofoil peak suction, γ = 1.4 · hot-gas
• The jet a cone sprays sideways — any gas, Mach number and area ratio · nozzle-duct
• The jet a cone sprays sideways — supersonic exits, γ = 1.2 · nozzle-duct
• The jet a cone sprays sideways — supersonic exits, γ = 1.2, ambient 0.01 of the chamber pressure · nozzle-duct
• The jet a cone sprays sideways — supersonic source flow, exit area ratio 25, any gas · nozzle-duct
• The jump does not ask what made it — a Mach 2 normal shock in a gas with gamma = 1.4 · structure-and-mixture · hero
• The jump does not ask what made it — gamma = 1.4, Mach 2 · structure-and-mixture
• The jump does not ask what made it — a Mach 2 normal shock in a gas with gamma = 1.4 · structure-and-mixture
• The jump does not ask what made it — Mach 2, gamma = 1.4 · structure-and-mixture
• The jump does not ask what made it — Mach 2 · structure-and-mixture
• The jump does not ask what made it — Mach 2, Pr = 3/4 · structure-and-mixture
• The jump does not ask what made it — Mach 2, constant viscosity · structure-and-mixture
• The jump does not ask what made it — Mach 2, Pr = 3/4, constant viscosity · structure-and-mixture
• The jump does not ask what made it — Mach 2 · structure-and-mixture
• The jump does not ask what made it — Mach 2 · structure-and-mixture
• The jump does not ask what made it — Mach 2 · structure-and-mixture
• The least drag a volume can have — L = 1, V = 0.02 for every body — supersonic, slender, at zero incidence · nonlinear-wave · hero
• The least drag a volume can have — L = 1, V = 0.02 for every body — supersonic, slender, at zero incidence · nonlinear-wave
• The least drag a volume can have — L = 1, V = 0.03 for every body — supersonic, slender, at zero incidence · nonlinear-wave
• The length the limit invents — a supersonic outer flow, Ackeret's interaction law, lambda = 1 · ideal-limit
• The paint that measures the wrong field — any Mach number — a calibration model, with the coefficients prescribed · optical-response · hero
• The paint that measures the wrong field — any Mach number — a calibration model, with the coefficients prescribed · optical-response
• The paint that measures the wrong field — any Mach number — a calibration model, with the coefficients prescribed · optical-response
• The paint that measures the wrong field — any Mach number — a calibration model, with the coefficients prescribed · optical-response
• The paint that measures the wrong field — any Mach number — a calibration model, with the coefficients prescribed · optical-response
• The paint that measures the wrong field — any Mach number — a calibration model, with the coefficients prescribed · optical-response
• The sound now is the source then — Mach 0.8, closest approach 100 m, sound speed 340 m/s · what-a-gas-carries-forward · hero
• The sound now is the source then — Mach 0.8, closest approach 100 m, sound speed 340 m/s · what-a-gas-carries-forward
• The sound now is the source then — Mach 0.8, closest approach 100 m · what-a-gas-carries-forward
• The sound now is the source then — Mach 1.6, closest approach 100 m · what-a-gas-carries-forward
• The sound that only leaves — source Mach numbers 0.3 to 0.8 · subsonic motion, uniform medium · noise-scaling
• The spot a local theory cannot see — perfect gas, γ = 1.4; jet ends in a normal shock at its own Mach number; jet interior not modelled · newtonian-lift · hero
• The spot a local theory cannot see — Mach 8; perfect gas, γ = 1.4; jet ends in a normal shock at its own Mach number; jet interior not modelled · newtonian-lift
• The spot a local theory cannot see — Mach 8, incident turn 10°; perfect gas, γ = 1.4; jet ends in a normal shock at its own Mach number; jet interior not modelled · newtonian-lift
• The spot a local theory cannot see — perfect gas, γ = 1.4; jet ends in a normal shock at its own Mach number; jet interior not modelled · newtonian-lift
• The spot a local theory cannot see — perfect gas, γ = 1.4; jet ends in a normal shock at its own Mach number; jet interior not modelled · newtonian-lift
• The spot a local theory cannot see — Mach 8; perfect gas, γ = 1.4; jet ends in a normal shock at its own Mach number; jet interior not modelled · newtonian-lift
• The spot a local theory cannot see — perfect gas, γ = 1.4; jet ends in a normal shock at its own Mach number; jet interior not modelled · newtonian-lift
• The sweep a root does not have — Ma below the critical value — an infinite yawed wing, inviscid · circulation-ledger
• The throat that stops listening — Ma up to 1.40 — cone angle measured off the circles · sound-signal
• The wall that cancels its own waves — steady supersonic flow — isentropic and irrotational, at the design point · moc-nozzle
• The wing the equation is really solving — linearised compressible flow, Ma ≤ 0.9 · elliptic planform · shape-from-pressure · hero
• The wing the equation is really solving — linearised compressible flow, Ma ≤ 0.9 · elliptic planform · shape-from-pressure
• The wing the equation is really solving — linearised compressible flow, Ma ≤ 0.9 · elliptic planform · shape-from-pressure
• The wing the equation is really solving — linearised compressible flow, Ma ≤ 0.9 · elliptic planform · shape-from-pressure
• Two totals, one of which a shock cannot touch — air, constant area, adiabatic, inlet Mach 0.3 · what-a-gas-carries-forward
• Two totals, one of which a shock cannot touch — air, constant area, frictionless, inlet Mach 0.3 · what-a-gas-carries-forward
• What a signal travels at — Ma up to 1.60 — cone angle measured off the circles · sound-signal
• What the airspeed indicator believes — subsonic and shock-free — each curve ends at its own section's critical Mach · pitot-error
• When a shock cannot bounce — γ = 1.4, steady flow — the domain is a property of the equations · reactive-shock
• When the warning cannot arrive — Ma up to 2.00 — cone angle measured off the circles · sound-signal · hero
• When the warning cannot arrive — Ma up to 2.00 — cone angle measured off the circles · sound-signal
• When the warning cannot arrive — Ma up to 2.40 — cone angle measured off the circles · sound-signal
• When the warning cannot arrive — Ma up to 4.00 — cone angle measured off the circles · sound-signal
• When the warning cannot arrive — Ma up to 1.05 — cone angle measured off the circles · sound-signal
• Which speed goes in the number — subsonic and shock-free — each curve ends at its own section's critical Mach · pitot-error · hero
• Which speed goes in the number — subsonic and shock-free — each curve ends at its own section's critical Mach · pitot-error

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