Set by the Mach number

• A blunted cone eats its nose's sheath in a few hundred radii — Mach 15; cone half-angle 7°, and a sphere-cylinder of the same nose · nonlinear-wave · hero
• A blunted cone eats its nose's sheath in a few hundred radii — Mach 15, cone half-angle 7°; entropy rise per streamline · nonlinear-wave
• A blunted cone eats its nose's sheath in a few hundred radii — Mach 15, cone half-angle 7°, laminar · nonlinear-wave
• A blunted cone eats its nose's sheath in a few hundred radii — Mach 15; cone half-angle 7°, and a sphere-cylinder of the same nose · nonlinear-wave
• A blunted cone eats its nose's sheath in a few hundred radii — Mach 15, laminar · nonlinear-wave
• A blunted cone eats its nose's sheath in a few hundred radii — Mach 15, cone half-angle 7°, Reₙ = 10⁵, laminar · nonlinear-wave
• A blunted cone eats its nose's sheath in a few hundred radii — Mach 15, a 7° cone two metres long · nonlinear-wave
• A blunted cone eats its nose's sheath in a few hundred radii — Mach 15, cone half-angle 7° · nonlinear-wave
• 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 cone intake's shock sees the whole capture — Mach 1.5 to 4, γ = 1.4; inviscid, cowl lip on the shock, no diffuser loss · normal-shock · hero
• A cone intake's shock sees the whole capture — Mach 1.5 to 4, γ = 1.4; inviscid, cowl lip on the shock, no diffuser loss · normal-shock
• A cone intake's shock sees the whole capture — Mach 1.5 to 4, γ = 1.4; inviscid, cowl lip on the shock, no diffuser loss · normal-shock
• A cone intake's shock sees the whole capture — Mach 1.5 to 4, γ = 1.4; inviscid, cowl lip on the shock, no diffuser loss · normal-shock
• A cone intake's shock sees the whole capture — Mach 1.5 to 4, γ = 1.4; inviscid, cowl lip on the shock, no diffuser loss · normal-shock
• A cone intake's shock sees the whole capture — Mach 1.5 to 4, γ = 1.4; inviscid, cowl lip on the shock, no diffuser loss · normal-shock
• A cone intake's shock sees the whole capture — Mach 1.5 to 4, γ = 1.4; inviscid, cowl lip on the shock, no diffuser loss · normal-shock
• A drag that needs a discontinuity — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• A drag that needs a discontinuity — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• A drag that needs a discontinuity — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• 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 flap that closes the mouth starts Busemann's biplane below its design point — Mach 1.05 to 2.6; elements 3% thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section · hero
• A flap that closes the mouth starts Busemann's biplane below its design point — Mach 1.05 to 2.6; elements 3% thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section
• A flap that closes the mouth starts Busemann's biplane below its design point — Mach 1.72 to 2.15 at the start, as the deflection is dialled; elements to scale · supersonic-section
• A flap that closes the mouth starts Busemann's biplane below its design point — Mach 1.05 to 2.6; elements 3% thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section
• A flap that closes the mouth starts Busemann's biplane below its design point — Mach 1.05 to 2.6; elements 3% thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section
• A flap that closes the mouth starts Busemann's biplane below its design point — Mach 1.05 to 2.6; elements 3% thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section
• A flap that closes the mouth starts Busemann's biplane below its design point — Mach 1.05 to 2.6; elements 3% thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section
• 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
• A shock that will not stand still — a shock at 0.6 of the chord with Mach 0.95 behind it · transonic
• A shock that will not stand still — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• A shock that will not stand still — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• Above their resonance, bubbles make water faster — air bubbles in water — the speed of sound in a mixture; linear, dilute; R = 1 mm · structure-and-mixture · hero
• Above their resonance, bubbles make water faster — air bubbles in water — the speed of sound in a mixture; linear, dilute · structure-and-mixture
• Above their resonance, bubbles make water faster — air bubbles in water — the speed of sound in a mixture; linear, dilute; R = 1 mm · structure-and-mixture
• Above their resonance, bubbles make water faster — air bubbles in water — the speed of sound in a mixture; linear, dilute; R = 1 mm · structure-and-mixture
• Above their resonance, bubbles make water faster — air bubbles in water — the speed of sound in a mixture; linear, dilute; R = 1 mm; damping removed · structure-and-mixture
• Above their resonance, bubbles make water faster — air bubbles in water — the speed of sound in a mixture; linear, dilute; α = 10⁻³ · structure-and-mixture
• Above their resonance, bubbles make water faster — air bubbles in water — the speed of sound in a mixture; linear, dilute · structure-and-mixture
• Above their resonance, bubbles make water faster — air bubbles in water — the speed of sound in a mixture; linear, dilute · structure-and-mixture
• 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
• An overexpanded nozzle lets go before its shock arrives — supersonic diverging part; area ratio 40, γ = 1.2; NPR is chamber over ambient pressure · nozzle-duct · hero
• An overexpanded nozzle lets go before its shock arrives — supersonic diverging part; area ratio 40, γ = 1.2; NPR is chamber over ambient pressure · nozzle-duct
• An overexpanded nozzle lets go before its shock arrives — supersonic diverging part; area ratio 40, γ = 1.2; NPR is chamber over ambient pressure · nozzle-duct
• An overexpanded nozzle lets go before its shock arrives — supersonic diverging part; area ratio 40, γ = 1.2; NPR is chamber over ambient pressure · nozzle-duct
• An overexpanded nozzle lets go before its shock arrives — supersonic diverging part; area ratio 40, γ = 1.2; NPR is chamber over ambient pressure · nozzle-duct
• An overexpanded nozzle lets go before its shock arrives — supersonic diverging part; area ratio 40, γ = 1.2; NPR is chamber over ambient pressure · nozzle-duct
• An overexpanded nozzle lets go before its shock arrives — supersonic diverging part; area ratio 40, γ = 1.2; NPR is chamber over ambient pressure · nozzle-duct
• Busemann's biplane has to be flown past its design point — each element 3% of its chord thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section · hero
• Busemann's biplane has to be flown past its design point — each element 3% of its chord thick, gap 0.3 chords; γ = 1.4; inviscid; Mach lines in linear theory · supersonic-section
• Busemann's biplane has to be flown past its design point — each element 3% of its chord thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section
• Busemann's biplane has to be flown past its design point — each element 3% of its chord thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section
• Busemann's biplane has to be flown past its design point — each element 3% thick; γ = 1.4 · supersonic-section
• Busemann's biplane has to be flown past its design point — γ = 1.4; linear design rule G = c / 2√(M² − 1) · supersonic-section
• Busemann's biplane has to be flown past its design point — each element 3% of its chord thick, gap 0.3 chords; γ = 1.4; inviscid · supersonic-section
• Busemann's biplane lifts only on its outer faces, and its channel turns the lift into a quarter-chord load — Mach 1.3 to 2.6; elements 3% thick, gap 0.3 chords; incidence to 5°; inviscid · supersonic-section · hero
• Busemann's biplane lifts only on its outer faces, and its channel turns the lift into a quarter-chord load — Mach 1.3 to 2.6; elements 3% thick, gap 0.3 chords; incidence to 5°; inviscid · supersonic-section
• Busemann's biplane lifts only on its outer faces, and its channel turns the lift into a quarter-chord load — Mach 1.3 to 2.6; elements 3% thick, gap 0.3 chords; incidence to 5°; inviscid · supersonic-section
• Busemann's biplane lifts only on its outer faces, and its channel turns the lift into a quarter-chord load — Mach 1.3 to 2.6; elements 3% thick, gap 0.3 chords; incidence to 5°; inviscid · supersonic-section
• Busemann's biplane lifts only on its outer faces, and its channel turns the lift into a quarter-chord load — Mach 1.3 to 2.6; elements 3% thick, gap 0.3 chords; incidence to 5°; inviscid · supersonic-section
• Busemann's biplane lifts only on its outer faces, and its channel turns the lift into a quarter-chord load — Mach 1.3 to 2.6; elements 3% thick, gap 0.3 chords; incidence to 5°; inviscid · supersonic-section
• Busemann's biplane lifts only on its outer faces, and its channel turns the lift into a quarter-chord load — Mach 1.3 to 2.6; elements 3% thick, gap 0.3 chords; incidence to 5°; inviscid · supersonic-section
• Busemann's biplane lifts only on its outer faces, and its channel turns the lift into a quarter-chord load — Mach 1.3 to 2.6; elements 3% thick, gap 0.3 chords; incidence to 5°; inviscid · supersonic-section
• Carburettor ice is made by the fuel, not the venturi — petrol at air–fuel ratio 12.5, all evaporated unless stated; 85 kPa, throat Mach below 0.3 · venturi-claim · hero
• Carburettor ice is made by the fuel, not the venturi — petrol at air–fuel ratio 12.5, all evaporated unless stated; 85 kPa, throat Mach below 0.3 · venturi-claim
• Carburettor ice is made by the fuel, not the venturi — petrol at air–fuel ratio 12.5, all evaporated unless stated; 85 kPa, throat Mach below 0.3 · venturi-claim
• Carburettor ice is made by the fuel, not the venturi — petrol at air–fuel ratio 12.5, all evaporated unless stated; 85 kPa, throat Mach below 0.3 · venturi-claim
• Carburettor ice is made by the fuel, not the venturi — petrol at air–fuel ratio 12.5, all evaporated unless stated; 85 kPa, throat Mach below 0.3 · venturi-claim
• Carburettor ice is made by the fuel, not the venturi — petrol at air–fuel ratio 12.5, all evaporated unless stated; 85 kPa, throat Mach below 0.3 · venturi-claim
• Carburettor ice is made by the fuel, not the venturi — petrol at air–fuel ratio 12.5, all evaporated unless stated; 85 kPa, throat Mach below 0.3 · venturi-claim
• Compression behind the lip is bought by opening the throat — Mach 2 to 5 — inviscid, perfect gas, mixed compression · normal-shock · hero
• Compression behind the lip is bought by opening the throat — Mach 2 to 5 — inviscid, perfect gas, mixed compression · normal-shock
• Compression behind the lip is bought by opening the throat — Mach 2 to 5 — inviscid, perfect gas, mixed compression · normal-shock
• Compression behind the lip is bought by opening the throat — Mach 2 to 5 — inviscid, perfect gas, mixed compression · normal-shock
• Compression behind the lip is bought by opening the throat — Mach 3, three external shocks, duct started open, throat at Mach 1.2 or above · normal-shock
• Compression behind the lip is bought by opening the throat — Mach 3 — inviscid, perfect gas, mixed compression · normal-shock
• Compression behind the lip is bought by opening the throat — Mach 2 to 5 — inviscid, perfect gas, mixed compression · normal-shock
• Compression behind the lip is bought by opening the throat — Mach 2 to 5 — inviscid, perfect gas, mixed compression · normal-shock
• 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 curve for every thickness — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic · hero
• One curve for every thickness — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• One curve for every thickness — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• One curve for every thickness — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• One curve for every thickness — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• One curve for every thickness — a thin parabolic arc at zero lift — inviscid, small perturbations, no boundary layer · transonic
• One curve for every thickness — M∞ = 0.85, γ = 1.4 — the pressure distribution is a shape, not a solution · hot-gas
• 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 cowl caps what the ramps can buy — Mach 3 — inviscid, perfect gas, external compression · normal-shock · hero
• The cowl caps what the ramps can buy — Mach 3 — inviscid, perfect gas, external compression · normal-shock
• The cowl caps what the ramps can buy — Mach 3 — inviscid, perfect gas, external compression · normal-shock
• The cowl caps what the ramps can buy — Mach 1.5 to 4.5 — inviscid, perfect gas, external compression · normal-shock
• The cowl caps what the ramps can buy — Mach 2 to 4 — inviscid, perfect gas, external compression · normal-shock
• The cowl caps what the ramps can buy — Mach 2 and 3 — inviscid, perfect gas · normal-shock
• The cowl caps what the ramps can buy — Mach 2 to 4 — inviscid, perfect gas, external compression · normal-shock
• 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 drag that can only see one curve — a slender body in a supersonic stream — linearised, inviscid, no lift · outer-boundary · hero
• The drag that can only see one curve — a slender body in a supersonic stream — linearised, inviscid, no lift · outer-boundary
• The drag that can only see one curve — a slender body in a supersonic stream — linearised, inviscid, no lift · outer-boundary
• The drag that can only see one curve — a slender body in a supersonic stream — linearised, inviscid, no lift · outer-boundary
• The drag that can only see one curve — a slender body in a supersonic stream — linearised, inviscid, no lift · outer-boundary
• The drag that can only see one curve — a slender body in a supersonic stream — linearised, inviscid, no lift · outer-boundary
• 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 gas a reflected shock refuses is inside the layer — shock Mach 1.1 to 12 into air at 300 K, calorically perfect; the wall at the fill temperature · shock-tube · hero
• The gas a reflected shock refuses is inside the layer — shock Mach 1.1 to 12 into air at 300 K, calorically perfect; the wall at the fill temperature · shock-tube
• The gas a reflected shock refuses is inside the layer — shock Mach 1.1 to 12 into air at 300 K, calorically perfect; the wall at the fill temperature · shock-tube
• The gas a reflected shock refuses is inside the layer — shock Mach 1.1 to 12 into air at 300 K, calorically perfect; the wall at the fill temperature · shock-tube
• The gas a reflected shock refuses is inside the layer — shock Mach 1.1 to 12 into air at 300 K, calorically perfect; the wall at the fill temperature · shock-tube
• The gas a reflected shock refuses is inside the layer — shock Mach 1 to 12 into a perfect gas at 300 K, γ 1.15 to 5/3; the wall at the fill temperature · shock-tube
• The gas a reflected shock refuses is inside the layer — shock Mach 1.1 to 12 into air at 300 K, calorically perfect; the wall at the fill temperature · shock-tube
• 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 last shock should be the weakest — Mach 2 to 4 — inviscid, perfect gas, external compression · normal-shock · hero
• The last shock should be the weakest — Mach 2 to 4 — inviscid, perfect gas, external compression · normal-shock
• The last shock should be the weakest — Mach 3 — inviscid, perfect gas, external compression · normal-shock
• The last shock should be the weakest — Mach 2 to 4 — inviscid, perfect gas, external compression · normal-shock
• The last shock should be the weakest — Mach 3 — inviscid, perfect gas, external compression · normal-shock
• The last shock should be the weakest — Mach 3 — inviscid, perfect gas, external compression · normal-shock
• The last shock should be the weakest — Mach 2 to 4 — inviscid, perfect gas, external compression · normal-shock
• The last shock should be the weakest — Mach 2 to 4 — inviscid, perfect gas, external compression · normal-shock
• 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 more small bubbles a cloud holds, the later it turns fast — air bubbles in water — the speed of sound in a mixture; 10 µm–1 mm, α = 10⁻³ · structure-and-mixture · hero
• The more small bubbles a cloud holds, the later it turns fast — air bubbles in water — the speed of sound in a mixture; 10 µm–1 mm, α = 10⁻³ · structure-and-mixture
• The more small bubbles a cloud holds, the later it turns fast — air bubbles in water — the speed of sound in a mixture; 10 µm–1 mm, α = 10⁻³; 30 kHz · structure-and-mixture
• The more small bubbles a cloud holds, the later it turns fast — air bubbles in water — the speed of sound in a mixture; 10 µm–1 mm, α = 10⁻³ · structure-and-mixture
• The more small bubbles a cloud holds, the later it turns fast — air bubbles in water — the speed of sound in a mixture; 10 µm–1 mm, α = 10⁻³; usable: <27% loss per wavelength · structure-and-mixture
• The more small bubbles a cloud holds, the later it turns fast — air bubbles in water — the speed of sound in a mixture; 10 µm–1 mm, α = 10⁻³ · structure-and-mixture
• The more small bubbles a cloud holds, the later it turns fast — air bubbles in water — the speed of sound in a mixture; 10 µm–1 mm, α = 10⁻³ · structure-and-mixture
• 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 shock that passes without an echo — shock Mach 1 to 8, calorically perfect gases — no vibration, no dissociation, no viscosity · shock-tube · hero
• The shock that passes without an echo — shock Mach 1 to 8, calorically perfect gases — no vibration, no dissociation, no viscosity · shock-tube
• The shock that passes without an echo — shock Mach 1 to 8, calorically perfect gases — no vibration, no dissociation, no viscosity · shock-tube
• The shock that passes without an echo — shock Mach 1 to 8, calorically perfect gases — no vibration, no dissociation, no viscosity · shock-tube
• The shock that passes without an echo — shock Mach 1 to 8, calorically perfect gases — no vibration, no dissociation, no viscosity · shock-tube
• The shock that passes without an echo — shock Mach 1 to 8, calorically perfect gases — no vibration, no dissociation, no viscosity · shock-tube
• The shock that passes without an echo — shock Mach 1 to 8, calorically perfect gases — no vibration, no dissociation, no viscosity · shock-tube
• 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 throttle plate is a wet bulb for petrol — petrol at air–fuel ratio 12.5, half evaporated into the stream; 85 kPa, throat Mach below 0.3, a 3 cm plate at 100 m/s; 80 per cent humidity · venturi-claim · hero
• The throttle plate is a wet bulb for petrol — petrol at air–fuel ratio 12.5, half evaporated into the stream; 85 kPa, throat Mach below 0.3, a 3 cm plate at 100 m/s; 80 per cent humidity · venturi-claim
• The throttle plate is a wet bulb for petrol — petrol at air–fuel ratio 12.5, half evaporated into the stream; 85 kPa, throat Mach below 0.3, a 3 cm plate at 100 m/s; 20 °C, 80 per cent · venturi-claim
• The throttle plate is a wet bulb for petrol — petrol at air–fuel ratio 12.5, half evaporated into the stream; 85 kPa, throat Mach below 0.3, a 3 cm plate at 100 m/s; 20 °C, 80 per cent · venturi-claim
• The throttle plate is a wet bulb for petrol — petrol at air–fuel ratio 12.5, half evaporated into the stream; 85 kPa, throat Mach below 0.3, a 3 cm plate at 100 m/s · venturi-claim
• The throttle plate is a wet bulb for petrol — petrol at air–fuel ratio 12.5, half evaporated into the stream; 85 kPa, throat Mach below 0.3, a 3 cm plate at 100 m/s; ice density 917 kg/m³ · venturi-claim
• The throttle plate is a wet bulb for petrol — petrol at air–fuel ratio 12.5, half evaporated into the stream; 85 kPa, throat Mach below 0.3, a 3 cm plate at 100 m/s · venturi-claim
• The wall that cancels its own waves — steady supersonic flow — isentropic and irrotational, at the design point · moc-nozzle
• The warm side pulls a bubble with no force on it — gradient 1 K/mm; Ma = |dσ/dT|Ga²/(μα), Re = ρ|dσ/dT|Ga²/μ² · moving-surface
• 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
• Thickness costs a fuselage far less than a wing — Mach 0 and 0.8, linearised — Prandtl–Glauert in the plane, Göthert in space · sphere-flow
• 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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