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

• A cold wall holds its layer on longer — laminar; Pr = 1, Chapman–Rubesin 1; edge speed ∝ xᵐ, β = 2m/(m + 1); wall enthalpy ratio gw · thermal-layer · hero
• A cold wall holds its layer on longer — laminar; Pr = 1, Chapman–Rubesin 1; edge speed ∝ xᵐ, β = 2m/(m + 1); wall enthalpy ratio gw · thermal-layer
• A cold wall holds its layer on longer — laminar; Pr = 1, Chapman–Rubesin 1; edge speed ∝ xᵐ, β = 2m/(m + 1); wall enthalpy ratio gw · thermal-layer
• A cold wall holds its layer on longer — laminar; Pr = 1, Chapman–Rubesin 1; edge speed ∝ xᵐ, β = 2m/(m + 1); wall enthalpy ratio gw · thermal-layer
• A cold wall holds its layer on longer — laminar; Pr = 1, Chapman–Rubesin 1; edge speed ∝ xᵐ, β = 2m/(m + 1); wall enthalpy ratio gw; Mₑ = 5 · thermal-layer
• A cold wall holds its layer on longer — laminar; Pr = 1, Chapman–Rubesin 1; edge speed ∝ xᵐ, β = 2m/(m + 1); wall enthalpy ratio gw; stagnation point · thermal-layer
• A cold wall holds its layer on longer — laminar; Pr = 1, Chapman–Rubesin 1; edge speed ∝ xᵐ, β = 2m/(m + 1); wall enthalpy ratio gw · thermal-layer
• A cold wall holds its layer on longer — laminar; Pr = 1, Chapman–Rubesin 1; edge speed ∝ xᵐ, β = 2m/(m + 1); wall enthalpy ratio gw · thermal-layer
• 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 released from a gradient overshoots the shape it left — air at 30 m/s; a 23 mm layer decelerated from x = 1 m as power m = −0.3, released at 1.6 m · overlap-layer · hero
• A layer released from a gradient overshoots the shape it left — air at 30 m/s; a 23 mm layer decelerated from x = 1 m as power m = −0.3, released at 1.6 m · overlap-layer
• A layer released from a gradient overshoots the shape it left — air at 30 m/s; a 23 mm layer decelerated from x = 1 m as power m = −0.3, released at 1.6 m · overlap-layer
• A layer released from a gradient overshoots the shape it left — air at 30 m/s; a 23 mm layer decelerated from x = 1 m as power m = −0.3, released at 1.6 m · overlap-layer
• A layer released from a gradient overshoots the shape it left — air at 30 m/s; a 23 mm layer decelerated from x = 1 m as power m = −0.3, released at 1.6 m · overlap-layer
• A layer released from a gradient overshoots the shape it left — air at 30 m/s; flat release (heavy) and one accelerating as the power 0.2 (amber), at 1.6 m · overlap-layer
• A layer released from a gradient overshoots the shape it left — air at 30 m/s; a 23 mm layer decelerated from x = 1 m as power m = −0.3, released at 1.6 m · overlap-layer
• A layer that is an integral of everything upstream — the two distributions above, up to the station · how-long-viscosity-remembers
• A layer whose stress lags the gradient separates sooner — air at 30 m/s, a flat-plate layer 23 mm thick meeting at x = 1 m an outer speed falling as the power m of 1 + (x − 1 m)/0.4 m · overlap-layer · hero
• A layer whose stress lags the gradient separates sooner — air at 30 m/s, a flat-plate layer 23 mm thick meeting at x = 1 m an outer speed falling as the power m of 1 + (x − 1 m)/0.4 m · overlap-layer
• A layer whose stress lags the gradient separates sooner — air at 30 m/s, a flat-plate layer 23 mm thick meeting at x = 1 m an outer speed falling as the power m of 1 + (x − 1 m)/0.4 m · overlap-layer
• A layer whose stress lags the gradient separates sooner — air at 30 m/s, a flat-plate layer 23 mm thick meeting at x = 1 m an outer speed falling as the power m of 1 + (x − 1 m)/0.4 m · overlap-layer
• A layer whose stress lags the gradient separates sooner — air at 30 m/s, a flat-plate layer 23 mm thick meeting at x = 1 m an outer speed falling as the power m of 1 + (x − 1 m)/0.4 m · overlap-layer
• A layer whose stress lags the gradient separates sooner — air at 30 m/s, a flat-plate layer 23 mm thick meeting at x = 1 m an outer speed falling as the power m of 1 + (x − 1 m)/0.4 m · overlap-layer
• A layer whose stress lags the gradient separates sooner — air at 30 m/s, a flat-plate layer 23 mm thick meeting at x = 1 m an outer speed falling as the power m of 1 + (x − 1 m)/0.4 m · overlap-layer
• A layer with a kink in it — the last profile has zero slope at the wall · bl-profile
• A layer's memory of one gradient helps it through the next, unless the next comes too soon — air at 30 m/s; decelerated as power −0.3 from 1 m to 1.6 m, released, decelerated again as power −0.4 · overlap-layer · hero
• A layer's memory of one gradient helps it through the next, unless the next comes too soon — air at 30 m/s; decelerated as power −0.3 from 1 m to 1.6 m, released, decelerated again as power −0.4 · overlap-layer
• A layer's memory of one gradient helps it through the next, unless the next comes too soon — air at 30 m/s; decelerated as power −0.3 from 1 m to 1.6 m, released, decelerated again as power −0.4 · overlap-layer
• A layer's memory of one gradient helps it through the next, unless the next comes too soon — air at 30 m/s; decelerated as power −0.3 from 1 m to 1.6 m, released, decelerated again as power −0.4 · overlap-layer
• A layer's memory of one gradient helps it through the next, unless the next comes too soon — air at 30 m/s; decelerated as power −0.3 from 1 m to 1.6 m, released, decelerated again as power −0.4 · overlap-layer
• A layer's memory of one gradient helps it through the next, unless the next comes too soon — air at 30 m/s; two decelerations of the powers marked, a release between · overlap-layer
• A layer's memory of one gradient helps it through the next, unless the next comes too soon — air at 30 m/s; decelerated as power −0.3 from 1 m to 1.6 m, released, decelerated again as power −0.4 · overlap-layer
• 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
• Followed rather than held, the parcels near a wing nearly tie — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil · hero
• Followed rather than held, the parcels near a wing nearly tie — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil
• Followed rather than held, the parcels near a wing nearly tie — thin cambered section at 4°, chord Reynolds number 10⁶; heights capped at four thicknesses · aerofoil
• Followed rather than held, the parcels near a wing nearly tie — thin cambered section at 4°, chord Reynolds number 10⁶ · aerofoil
• Followed rather than held, the parcels near a wing nearly tie — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil
• Followed rather than held, the parcels near a wing nearly tie — thin cambered section at 4°; chord Reynolds numbers 3·10⁵ to 3·10⁶ · aerofoil
• Followed rather than held, the parcels near a wing nearly tie — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil
• 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
• Laid flat, a warm plate is pushed by the pressure of its own layer — laminar natural convection on a slightly tilted plate; Pr 0.72 and 7 · regime-collapse
• 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 side that turns turbulent first decides who arrives first near the wall — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil · hero
• The side that turns turbulent first decides who arrives first near the wall — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil
• The side that turns turbulent first decides who arrives first near the wall — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil
• The side that turns turbulent first decides who arrives first near the wall — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil
• The side that turns turbulent first decides who arrives first near the wall — thin cambered section at 4° · aerofoil
• The side that turns turbulent first decides who arrives first near the wall — upper surface solid, lower dashed; 60% chord · aerofoil
• The side that turns turbulent first decides who arrives first near the wall — thin cambered section, 6% thickness parameter, 4% camber; chord Reynolds number 10⁶ unless stated · aerofoil
• 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

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