Boundary-layer theory — Re large enough that the layer is thin, and the number cancels

• A finite force from an infinite speed — external flow going as a power of distance · bl-profile
• A guess with a constant in it — flat plate, no pressure gradient · bl-profile
• A layer that is an integral of everything upstream — the two distributions above, up to the station · how-long-viscosity-remembers
• A layer with a kink in it — the last profile has zero slope at the wall · bl-profile
• A limit nothing reaches — a stated closure for the first, the exact similarity solution for the second · overlap-layer
• Ask for the pressure, and see what shape that is — external flow going as a power of distance · bl-profile
• Drag in the theory that forbids it — external flow going as a power of distance · bl-profile
• Every mode decays and it grows anyway — U = 30 m/s in air — transition placed at Re_x = 3e+6, observed · plate-friction
• Faster than the wind that drives it — chord Reynolds number 10⁶, laminar · drag-split
• How many things a flow must be told — flat plate, no pressure gradient · bl-profile
• How much uphill a layer can take — external flow going as a power of distance · bl-profile · hero
• How much uphill a layer can take — the last profile has zero slope at the wall · bl-profile
• How much uphill a layer can take — external flow going as a power of distance · bl-profile
• How much uphill a layer can take — flat plate, no pressure gradient · bl-profile
• How thick is thin — flat plate, no pressure gradient · bl-profile · hero
• How thick is thin — flat plate, no pressure gradient · bl-profile
• How thick is thin — the last profile has zero slope at the wall · bl-profile
• How thick is thin — flat plate, no pressure gradient · bl-profile
• How thick is thin — laminar, zero pressure gradient, ν = 10⁻⁵ m²/s at U = 1 m/s · bl-profile
• The air a wing does not carry — flat plate, no pressure gradient · bl-profile
• The air a wing does not carry — laminar, zero pressure gradient, ν = 10⁻⁵ m²/s at U = 1 m/s · bl-profile
• The air a wing does not carry — Re_x = 2.0e+6 — laminar, zero pressure gradient · bl-profile
• The air a wing does not carry — laminar similarity solutions — β from 1 to separation at −0.1988 · bl-profile
• The air a wing does not carry — flat plate, no pressure gradient · bl-profile
• The body the outer flow actually sees — laminar, zero pressure gradient, ν = 10⁻⁵ m²/s at U = 1 m/s · bl-profile · hero
• The body the outer flow actually sees — laminar, zero pressure gradient, ν = 10⁻⁵ m²/s at U = 1 m/s · bl-profile
• The body the outer flow actually sees — flat plate, no pressure gradient · bl-profile
• The body the outer flow actually sees — external flow going as a power of distance · bl-profile
• The body the outer flow actually sees — flat plate, no pressure gradient · bl-profile
• The cheapest way to stay up — flat plate, one side, no pressure gradient · drag-split
• The cheapest way to stay up — chord Reynolds number 10⁶, laminar · drag-split
• The cheapest way to stay up — chord Reynolds number 10⁶, laminar · drag-split
• The cost of going turbulent — U = 30 m/s in air — transition placed at Re_x = 5e+5, observed · plate-friction
• The layer that stops growing — U = 30 m/s in air — transition placed at Re_x = 5e+5, observed · plate-friction
• The number that is an answer — a laminar flat-plate boundary layer — Pr from 10⁻⁵ to 10³ · regime-collapse · hero
• The number that is an answer — a laminar flat-plate boundary layer — Blasius, Pr from 0.01 to 100 · regime-collapse
• The number that is an answer — a laminar flat-plate boundary layer — Pr from 10⁻⁵ to 10³ · regime-collapse
• The number that is an answer — a laminar flat-plate boundary layer — the exponent, not the coefficient · regime-collapse
• The number that is an answer — a laminar flat-plate boundary layer — Pr from 10⁻⁵ to 10³ · regime-collapse
• The number that is an answer — a laminar flat-plate boundary layer — the exponent, not the coefficient · regime-collapse
• The number that is an answer — a laminar flat-plate boundary layer, Pr from 10⁻⁵ to 10³ · regime-collapse
• The number that is not a number — U = 30 m/s in air — transition placed at Re_x = 5e+5, observed · plate-friction
• The number that is not a number — U = 30 m/s in air — transition placed at Re_x = 1e+5, observed · plate-friction
• The number that is not a number — U = 30 m/s in air — transition placed at Re_x = 3e+6, observed · plate-friction
• The skin that lags the flight — turbulent, Pr = 0.71 — the friction is a one-seventh-power correlation at Re_x = 10⁷ · thermal-layer · hero
• The skin that lags the flight — turbulent, Pr = 0.71 — the friction is a one-seventh-power correlation at Re_x = 10⁷ · thermal-layer
• The skin that lags the flight — turbulent, Pr = 0.71 — the friction is a one-seventh-power correlation at Re_x = 10⁷ · thermal-layer
• The skin that lags the flight — turbulent, Pr = 0.71 — the friction is a one-seventh-power correlation at Re_x = 10⁷ · thermal-layer
• The skin that lags the flight — turbulent, Pr = 0.71 — the recovery factor is 0.84 and the friction a correlation · thermal-layer
• The skin that lags the flight — turbulent, Pr = 0.71 — the recovery factor is 0.84 and the friction a correlation · thermal-layer
• The skin that lags the flight — turbulent, Pr = 0.71 — the friction is a one-seventh-power correlation at Re_x = 10⁷ · thermal-layer
• The solution that keeps its nonlinear term — water, nu = 10⁻⁶ m²/s; a disc at 100 rad/s, radius 0.2 m · oscillating-wall
• The solutions stop being chosen — U = 30 m/s in air — transition placed at Re_x = 5e+5, observed · plate-friction
• The third thickness — Re_x = 2.0e+6 — laminar, zero pressure gradient · bl-profile · hero
• The third thickness — Re_x = 2.0e+6 — laminar, zero pressure gradient · bl-profile
• The third thickness — laminar similarity solutions — β from 1 to separation at −0.1988 · bl-profile
• The third thickness — laminar, zero pressure gradient, ν = 10⁻⁵ m²/s at U = 1 m/s · bl-profile
• The third thickness — flat plate, no pressure gradient · bl-profile
• The two drags a wing pays — flat plate, one side, no pressure gradient · drag-split
• The two drags a wing pays — chord Reynolds number 10⁶, laminar · drag-split
• The wall that shakes — flat plate, no pressure gradient · bl-profile
• The wall that shakes — flat plate, no pressure gradient · bl-profile
• The wind a swept wing feels — laminar boundary layer — incompressible, on an infinite wing yawed at 35° · swept-wing · hero
• The wind a swept wing feels — laminar boundary layer — incompressible, on an infinite wing yawed at 35° · swept-wing
• The wind a swept wing feels — laminar boundary layer — incompressible, on an infinite wing yawed at 35° · swept-wing
• The wind a swept wing feels — laminar boundary layer — incompressible, on an infinite wing yawed at 45° · swept-wing
• Where the heat of a drag is made — Re_x = 2.0e+6 — laminar, zero pressure gradient · bl-profile
• Where the straight line stops — external flow going as a power of distance · bl-profile
• Where vorticity comes from — flat plate, no pressure gradient · bl-profile

Every regime · All figures · All essays