Swept in Mach number — the figure is about the variation, not one value

• The pocket on top of the wing — Ma 0.2 to 0.95 — first order, 10% thick at 2° · transonic · hero
• The pocket on top of the wing — Ma 0.2 to 0.95 — first order, 10% thick at 2° · transonic
• The pocket on top of the wing — Ma 0.2 to 0.95 — first order, 14% thick at 2° · transonic
• The pocket on top of the wing — Ma 0.2 to 0.95 — first order, 10% thick at 6° · transonic
• The pocket on top of the wing — Ma 0.2 to 0.95 — first order, 6% thick at 2° · transonic
• The wind a swept wing feels — Ma 0.2 to 0.95 — first order, 10% thick at 2° · transonic
• The wing the equation is really solving — Ma 0.2 to 0.95 — first order, 10% thick at 2° · transonic
• Three readings, and the one each answer leans on — Ma 0.1 to 0.95 — subsonic, γ = 1.4, 11 km (22632 Pa, 216.65 K) · thermal-layer · hero
• Three readings, and the one each answer leans on — Ma 0.1 to 0.95 — subsonic, γ = 1.4, 11 km (22632 Pa, 216.65 K) · thermal-layer
• Three readings, and the one each answer leans on — Ma 0.1 to 0.95 — subsonic, γ = 1.4, 11 km (22632 Pa, 216.65 K) · thermal-layer
• Three readings, and the one each answer leans on — Ma 0.1 to 0.95 — subsonic, γ = 1.4, 11 km (22632 Pa, 216.65 K) · thermal-layer
• Three readings, and the one each answer leans on — Ma 0.1 to 0.95 — subsonic, γ = 1.4, 11 km (22632 Pa, 216.65 K) · thermal-layer
• Three readings, and the one each answer leans on — Ma 0.1 to 0.95 — subsonic, γ = 1.4, sea level and 11 km · thermal-layer
• Three readings, and the one each answer leans on — Ma 0.1 to 0.95 — subsonic, γ = 1.4, 11 km (22632 Pa, 216.65 K) · thermal-layer
• Three readings, and the one each answer leans on — Ma 0.1 to 0.95 — subsonic, γ = 1.4, 11 km (22632 Pa, 216.65 K) · thermal-layer
• When a body tears the water — Ma 0.2 to 0.95 — first order, 10% thick at 2° · transonic
• Which speed goes in the number — Ma 0.2 to 0.95 — first order, 6% thick at 0° · transonic
• Which speed goes in the number — Ma 0.2 to 0.95 — first order, 10% thick at 2° · transonic
• Which speed goes in the number — Ma 0.2 to 0.95 — first order, 12% thick at 0° · transonic
• Which speed goes in the number — Ma 0.2 to 0.95 — first order, 12% thick at 6° · transonic
• Energy instead of pressure — Ma 0 to 1, γ = 1.4 · isentropic-curves
• The duct that works backwards — Ma 0 to 1 at the throat, γ = 1.4 · nozzle-duct
• The throat that stops listening — Ma 0 to 1 at the throat, γ = 1.4 · nozzle-duct · hero
• The throat that stops listening — Ma 0 to 1 at the throat, γ = 1.4 · nozzle-duct
• Two ways to choke — Ma 0 to 1 at the throat, γ = 1.4 · nozzle-duct
• What a signal travels at — Ma 0 to 1, γ = 1.4 · isentropic-curves
• What the airspeed indicator believes — Ma 0 to 1, γ = 1.4 · pitot-error · hero
• What the airspeed indicator believes — Ma 0 to 1, γ = 1.4 · pitot-error
• Which speed goes in the number — Ma 0 to 1, γ = 1.4 · isentropic-curves
• The thermometer that heats itself — Ma 0 to 1.1, adiabatic — no conduction down the stem and no radiation · thermal-layer · hero
• The thermometer that heats itself — Ma 0 to 1.1, adiabatic — no conduction down the stem and no radiation · thermal-layer
• The thermometer that heats itself — Ma 0 to 1.1, adiabatic — no conduction down the stem and no radiation · thermal-layer
• The thermometer that heats itself — Ma 0 to 1.1, adiabatic — no conduction down the stem and no radiation · thermal-layer
• The thermometer that heats itself — Ma 0 to 1.1, adiabatic — no conduction down the stem and no radiation · thermal-layer
• The thermometer that heats itself — Ma 0 to 1.1, adiabatic — no conduction down the stem and no radiation · thermal-layer
• The thermometer that heats itself — Ma 0 to 1.1, adiabatic — no conduction down the stem and no radiation · thermal-layer
• The carpet an accelerating aeroplane folds — Ma 1.15 to 1.9 — a standard atmosphere, 15 km, straight flight at constant acceleration · nonlinear-wave · hero
• The carpet an accelerating aeroplane folds — Ma 1.15 to 1.9 — 15 km, Mach 1.6 level against 1 m/s² through the transonic · nonlinear-wave
• The carpet an accelerating aeroplane folds — Ma 1.15 to 1.9 — a standard atmosphere, 15 km, straight flight at constant acceleration · nonlinear-wave
• The carpet an accelerating aeroplane folds — Ma 1.15 to 1.9 — 15 km, accelerating at 1 m/s² through the transonic · nonlinear-wave
• The carpet an accelerating aeroplane folds — Ma 1.15 to 1.9 — 15 km, a standard atmosphere, straight flight · nonlinear-wave
• The carpet an accelerating aeroplane folds — Ma 1.15 to 1.9 — a standard atmosphere, 1.5 m/s² along the track · nonlinear-wave
• The viscosity nobody uses — air at 20 °C, Ma 1.02 to 2 — weak-shock theory, and rarefied above about Ma 1.4 · noise-scaling
• What the airspeed indicator believes — Ma 0 to 2, γ = 1.4 · pitot-error
• The carpet an accelerating aeroplane folds — Ma 1.15 to 2.4 — a standard atmosphere, 15 km, straight down the track · nonlinear-wave
• The boom that turns back before the ground — Ma 1.1 to 2.5 — standard atmosphere and uniform air · nonlinear-wave
• The carpet an accelerating aeroplane folds — Ma 1.3 to 2.5 — 15 km, a standard atmosphere · nonlinear-wave
• The carpet an accelerating aeroplane folds — Ma 1.3 to 2.5 — 15 km, a standard atmosphere · nonlinear-wave
• The edge is a rumble, not a quieter bang — Ma 1.3 to 2.5 — 15 km, a standard atmosphere · nonlinear-wave
• The edge is a rumble, not a quieter bang — Ma 1.3 to 2.5 — 15 km, a standard atmosphere · nonlinear-wave
• The edge is a rumble, not a quieter bang — Ma 1.3 to 2.5 — 15 km, a standard atmosphere · nonlinear-wave
• The edge is a rumble, not a quieter bang — Ma 1.3 to 2.5 — 15 km, a standard atmosphere · nonlinear-wave
• A shock that leans — Ma 1 to 3 in front, γ = 1.4 · normal-shock
• Energy instead of pressure — Ma 0 to 3, γ = 1.4 · isentropic-curves · hero
• Energy instead of pressure — Ma 0 to 3, γ = 1.4 · isentropic-curves
• Energy instead of pressure — Ma 0 to 3, γ = 1.4 · isentropic-curves
• Energy instead of pressure — Ma 0 to 3, γ = 1.4 · isentropic-curves
• One area, two answers — Ma 0 to 3, γ = 1.4 · isentropic-curves
• Two totals, one of which a shock cannot touch — Ma 0 to 3, γ = 1.4 · isentropic-curves
• The jet a cone sprays sideways — supersonic, Ma 3.76 to 3.96 — area ratio 25, γ = 1.2, vacuum · nozzle-duct
• The only law that forbids it — Ma 1 to 4 in front, γ = 1.4 · normal-shock
• The only law that forbids it — Ma 1 to 4 in front, γ = 1.4 · normal-shock
• What a shock costs — Ma 2 to 4, γ = 1.4 · normal-shock
• What the airspeed indicator believes — Ma 1 to 4 — supersonic, where the probe makes its own shock · pitot-error
• What the airspeed indicator believes — Ma 1 to 4 — supersonic, where the probe makes its own shock · pitot-error
• A cone finishes its turn after the shock — Ma 1.5 to 5, γ = 1.4 — inviscid · normal-shock
• A shock that leans — Ma 1.5 to 5, γ = 1.4 · normal-shock
• Energy instead of pressure — Ma 0 to 5, γ = 1.4 · isentropic-curves
• One diaphragm, every wave — Ma 0.6 to 5 in front, γ = 1.4 · normal-shock
• One number decides which physics applies — Mach number from 0 to 5 · regime-axis
• The jump the equations allow — Ma 1 to 5 in front, γ = 1.4 · normal-shock
• The jump the equations allow — Ma 0.6 to 5 in front, γ = 1.4 · normal-shock
• The model that cannot be matched — Mach number from 0 to 5 · regime-axis
• The only law that forbids it — Ma 0.6 to 5 in front, γ = 1.4 · normal-shock · hero
• The only law that forbids it — Ma 0.6 to 5 in front, γ = 1.4 · normal-shock
• The Reynolds number, and the length in it — Mach number from 0 to 5 · regime-axis
• What a shock costs — Ma 1 to 5 in front, γ = 1.4 · normal-shock · hero
• What a shock costs — Ma 1 to 5 in front, γ = 1.4 · normal-shock
• What a shock costs — Ma 0.6 to 5 in front, γ = 1.4 · normal-shock
• When air stops being incompressible — Mach number from 0 to 5 · regime-axis · hero
• When air stops being incompressible — Mach number from 0 to 5 · regime-axis
• When the wedge is too blunt — Ma 1 to 5 in front, γ = 1.4 · normal-shock
• The wall that heats itself — Ma 0 to 6 at Pr = 0.71 — laminar flat plate, perfect gas, γ = 1.4 · thermal-layer · hero
• The wall that heats itself — Ma 0 to 6 at Pr = 0.71 — laminar flat plate, perfect gas, γ = 1.4 · thermal-layer
• When the wedge is too blunt — Ma 1.5 to 6, γ = 1.4 · normal-shock
• A shock that leans — Ma 1.5 to 8, γ = 1.4 · normal-shock
• The gradient the heat never hears — Ma 0 to 8, Te = 220 K — laminar, Pr = 1, constant properties · thermal-layer
• When the wedge is too blunt — Ma 2 to 8, γ = 1.4 · normal-shock
• A cone finishes its turn after the shock — Ma 1.15 to 10, γ = 1.4 — inviscid · normal-shock
• What a shock costs — Ma 1 to 12 in front, γ = 1.4 · normal-shock
• The edge is a rumble, not a quieter bang — Ma 1.8 — 15 km, a standard atmosphere · nonlinear-wave
• The face Newton left in shadow — Ma 3 to 20 — inviscid, two-dimensional, γ = 1.4 · newtonian-lift · hero
• The face Newton left in shadow — Ma 3 to 20 — inviscid, two-dimensional, γ = 1.4 · newtonian-lift
• The face Newton left in shadow — Ma 3 to 20 — inviscid, two-dimensional, γ = 1.4 · newtonian-lift
• The jump the equations allow — Ma 1 to 20 in front, γ = 1.4 · normal-shock
• The face Newton left in shadow — Ma 2.5 to 25 — inviscid pressures, friction 0.001 on both faces · newtonian-lift
• The face Newton left in shadow — Ma 1.6 to 25 — inviscid, two-dimensional, γ = 1.4 · newtonian-lift
• The face Newton left in shadow — Ma 2 to 60 — inviscid, two-dimensional, γ = 1.4 · newtonian-lift

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