Regime
Ma above 1.2 — supersonic
Every figure drawn under this hypothesis — 77 of them — with the essay each one belongs to and the generator that drew it.
77 figure placements state this regime. The strip along the foot of every figure names two things — the model that produced it and the regime it holds in — and this listing is read back out of the finished drawing rather than from what produced it.
- The only theory simple enough to optimise — hypersonic — the leeward face is shaded and carries nothing at all · newtonian-lift
- The theory that forbade flight — α = 5° · valid where the shock lies on the body, which is hypersonic · newtonian-lift
- The pocket on top of the wing — Ma 1.40 in front — supersonic, γ = 1.4 · normal-shock
- What a shock costs — Ma 1.40 in front — supersonic, γ = 1.4 · normal-shock
- The bubble that hammers — Ma 1.50 in front — supersonic, γ = 1.4 · normal-shock
- The wall that cancels its own waves — Ma 1.6 at the exit — the comparison is of two routes, not of two regimes · moc-nozzle
- One diaphragm, every wave — Ma 1.66 in front — supersonic, γ = 1.4 · normal-shock
- A cone finishes its turn after the shock — Ma 2, γ = 1.4 — inviscid, no boundary layer · normal-shock · hero
- A cone finishes its turn after the shock — Ma 2, γ = 1.4 — inviscid, no boundary layer · normal-shock
- A cone finishes its turn after the shock — Ma 2, γ = 1.4 — inviscid, no boundary layer · normal-shock
- A cone finishes its turn after the shock — Ma 2, γ = 1.4 — inviscid · normal-shock
- A cone finishes its turn after the shock — Ma 2, γ = 1.4 — inviscid · normal-shock
- A cone finishes its turn after the shock — Ma 2, γ = 1.4 — inviscid · normal-shock
- A shock that leans — Ma 2.00, θ = 10° — detachment at 23.0° · normal-shock · hero
- A shock that leans — Ma 2.00, θ = 10° — detachment at 23.0° · normal-shock
- A shock that leans — Ma 2.00 — detachment at 22.97° · normal-shock
- A shock that leans — Ma 2.00, 4° incidence, γ = 1.4 · supersonic-section
- Drag with nothing to rub — Ma 2.00, incidence 0.5° to 12°, γ = 1.4 · supersonic-section · hero
- Drag with nothing to rub — Ma 2.00, 5° incidence, γ = 1.4 · supersonic-section
- Drag with nothing to rub — Ma 2.00 in front, γ = 1.4 · expansion-fan
- Drag with nothing to rub — Ma 2.00, incidence 0.5° to 12°, γ = 1.4 · supersonic-section
- Drag with nothing to rub — Ma 2.00, 4° incidence, γ = 1.4 · supersonic-section
- Drag with nothing to rub — Ma 2.00, 5° incidence, γ = 1.4 · supersonic-section
- Energy instead of pressure — Ma 2.00 — detachment at 22.97° · normal-shock
- The jump the equations allow — Ma 2.00 in front — supersonic, γ = 1.4 · normal-shock · hero
- The jump the equations allow — Ma 2.00 in front — supersonic, γ = 1.4 · normal-shock
- The shock in a river — Ma 2.00 in front — supersonic, γ = 1.4 · normal-shock
- The theory that forbade flight — Ma 2.00, 5° incidence, γ = 1.4 · supersonic-section
- The viscosity nobody uses — Ma 2.00 in front — supersonic, γ = 1.4 · normal-shock
- Turning the other way is free — Ma 2.00, 10° either way, γ = 1.4 · expansion-fan · hero
- Turning the other way is free — Ma 2.00, 10° either way, γ = 1.4 · expansion-fan
- Turning the other way is free — Ma 2.00 in front, γ = 1.4 · expansion-fan
- Turning the other way is free — Ma 2.00 → 2.38, isentropic — γ = 1.4 · expansion-fan
- Turning the other way is free — Ma 2.00, 6° incidence, γ = 1.4 · supersonic-section
- What the airspeed indicator believes — Ma 2.00 in front — supersonic, γ = 1.4 · normal-shock
- When the warning cannot arrive — Ma 2.00 → 2.30, isentropic — γ = 1.4 · expansion-fan
- When the wedge is too blunt — Ma 2.00 — detachment at 22.97° · normal-shock · hero
- When the wedge is too blunt — Ma 2.00 — detachment at 22.97° · normal-shock
- The wall that cancels its own waves — Ma 2.4 at the exit — steady, isentropic, irrotational and inviscid · moc-nozzle · hero
- The wall that cancels its own waves — Ma 2.4 at the exit — steady, isentropic, irrotational and inviscid · moc-nozzle
- The wall that cancels its own waves — Ma 2.4 at the exit — steady, isentropic, irrotational supersonic flow · moc-nozzle
- The wall that cancels its own waves — Ma 2.4 at the exit — the comparison is of two routes, not of two regimes · moc-nozzle
- The wall that cancels its own waves — Ma 2.4 at the exit by the area rule in all three cases · moc-nozzle
- One area, two answers — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct · hero
- One area, two answers — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- One area, two answers — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- One area, two answers — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- One area, two answers — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The depth that costs least — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The duct that works backwards — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The duct that works backwards — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The duct that works backwards — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The jump the equations allow — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The only law that forbids it — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The throat that stops listening — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The throat that stops listening — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The throat that stops listening — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- What a shock costs — area ratio 2.5 — design exit Ma 2.44, γ = 1.4 · nozzle-duct
- The only law that forbids it — Ma 2.50 — detachment at 29.80° · normal-shock
- Drag with nothing to rub — Ma 3.00, 5° incidence, γ = 1.4 · supersonic-section
- The other layer, and the one number that separates them — Ma = 3, Pr = 0.71 — laminar flat plate, the flux linear in (T_aw − T_w) · thermal-layer
- The wall that heats itself — Ma = 3, Pr = 0.71 — laminar flat plate, the flux linear in (T_aw − T_w) · thermal-layer
- The wall that heats itself — Ma 3.00 in front — supersonic, γ = 1.4 · normal-shock
- Turning the other way is free — Ma 3.00 → 4.32, isentropic — γ = 1.4 · expansion-fan
- Turning the other way is free — Ma 3.00 in front, γ = 1.4 · expansion-fan
- When the wedge is too blunt — Ma 3.00 — detachment at 34.07° · normal-shock
- When the wedge is too blunt — Ma 3.00, 3° incidence, γ = 1.4 · supersonic-section
- The wall that cancels its own waves — Ma 3.2 at the exit — steady, isentropic, irrotational and inviscid · moc-nozzle
- The wall that cancels its own waves — Ma 3.2 at the exit — steady, isentropic, irrotational supersonic flow · moc-nozzle
- The jet a cone sprays sideways — Ma 3.92 on the cap — half-angle 15°, area ratio 25, γ = 1.2 · nozzle-duct · hero
- The jet a cone sprays sideways — Ma 3.92 on the cap — half-angle 15°, area ratio 25, γ = 1.2 · nozzle-duct
- The face Newton left in shadow — Ma 5 — inviscid, two-dimensional, γ = 1.4 · newtonian-lift
- The face Newton left in shadow — Ma 5 and 20 — inviscid pressures, friction 0.001 on both faces · newtonian-lift
- The gradient the heat never hears — Ma 5, Te = 220 K — laminar, Pr = 1, constant properties · thermal-layer · hero
- The gradient the heat never hears — Ma 5, Te = 220 K — laminar, Pr = 1, constant properties · thermal-layer
- The gradient the heat never hears — Ma 5, Te = 220 K — laminar, Pr = 1, constant properties · thermal-layer
- The jump the equations allow — Ma 5.00 in front — supersonic, γ = 1.4 · normal-shock