Fluid Flow & Aerodynamics
why things fly, and why the usual explanation is wrong
Concept

Munk stagger — where it appears

Munk's theorem that the total induced drag of a group of lifting surfaces is unchanged when they are moved fore and aft, their spans and loads fixed. It fixes a formation's total saving by its lateral spacing and leaves the stagger to decide only how that saving is shared.

Named by 5 essays across 2 fields — each of them below, with the objects they name alongside it.

A closed wake, and the loading of least drag on it. The wake of a box wing in the plane that decides its drag, with the circulation of least induced drag drawn as a thickness along it. The horizontal members carry a loading close to elliptic and the vertical ones carry a share that lifts nothing — they contribute no lift, since lift is Γ dy and dy is zero on a vertical, and they change the drag by changing where the wake's vorticity is. At a gap of 20 per cent of span this system costs 67.1 per cent of what a single wing of the same span and lift would.

A wake that closes on itself

Prandtl's best wing system is a rectangle, not a wing. Solving for the loading on a closed wake turns up a circulation that costs nothing and does nothing — a gauge freedom in the middle of an optimisation — and a drag that keeps falling with no floor under it.

circulation · Box wing The V in which every bird pays the same is curved. Nine birds one span apart, flying up the page, in plan: each short line is a wing, its height its distance behind the leader in spans. The straight V at 7.5° — the fairest straight V — and the V whose members' positions are solved so that every one pays exactly the same share of the induced drag. The equal-share arms leave the leader almost abreast and bend back ever more steeply: 1.6°, 7.6°, 17°, 32° from the apex to the tips.

A fair V is a curved V

In a straight V of birds somebody always pays more than somebody else: at the fairest angle the leader and the two birds at the tips pay half again what the birds between them pay. The V in which every bird pays exactly the same can be solved for, and it is not straight. Its arms leave the leader almost abreast and bend back ever more steeply, to thirty-two degrees at the tips of a flock of nine. The share every bird then pays is the flock's average, fixed by Munk's theorem before any position is chosen — so fairness costs nothing, and the only thing that can make the flock cheaper is flying closer together sideways.

circulation · Formation The drag is set by the split, and stability sets the split. The least induced drag of a wing and a smaller surface together, as a multiple of the elliptic wing's alone, against the share of the lift the smaller surface carries. By Munk's stagger theorem the curve is the same whichever surface is in front. Its minimum, 0.9984, is at a share of 1.9 per cent. At a static margin of a tenth of a chord, a tail trims with 6.7 per cent of the weight on it, upwards, and pays 1.009; a canard trims with 19 per cent and pays 1.128.

A canard pays for its stability in induced drag

The argument for a canard is that both of its surfaces lift upwards, while a tail pushes down and makes the wing carry the difference. Munk's stagger theorem turns the question into arithmetic: two surfaces' least induced drag depends only on how the lift is split between them, not on which is in front. Static margin sets the split. At a margin of a tenth of a chord a tail carries a small upload and costs under one per cent; a canard must carry a fifth of the weight on a third of the span and costs twelve, and the more stable it is made, the more it pays.

circulation · Moment One bowl, and a line across it for every way of flying. The least induced drag of a wing, a canard and a tail together, as a function of the canard's and the tail's shares of the lift, drawn as rings of equal drag about the bowl's foot, where each carries 1.9 per cent. A static margin of a tenth of a chord and a wing pitching moment draw a straight line of trimmed splits across the bowl. The tail aircraft trims where its line crosses the axis of zero canard load; the three-surface aircraft slides along the same line to the point nearest the foot.

A third surface is worth a square

A canard and a tail each leave an aircraft one free share of its lift, and the static margin spends it. Give an aircraft both and one share stays free after trim, so the split can slide along a line to the point of least induced drag. What that slide is worth turns out to be a square: half the bowl's curvature times the square of how far the tail aircraft already trims from twice the bowl's foot. For a cruising wing the saving is under one per cent and less than the canard's own skin friction; it pays only for a wing whose pitching moment is as large as a flapped section's.

circulation · Moment A phantom biplane partner doubles the induced drag. Induced drag at a given lift, as a multiple of its deep-water value, against the foil's depth in spans. The surface's image of the foil is an identical wing, equally loaded, twice the depth above it, so the real foil pays its own induced drag plus the mutual drag of a biplane with a gap of twice its depth: 1 + σ, with σ Prandtl's biplane factor. The elliptic biplane's 1 + σ and the aspect-ratio-9 foil's lattice both run to two as the depth closes.

A foil under the surface flies with a phantom

At foiling speed the water's surface cannot hold a pressure, and the image that condition requires is not the reversed one a wall makes. For a horizontal foil it is an identical wing, equally loaded, above the surface — a biplane partner that takes lift and gives nothing back, doubling the induced drag as the foil rises. For the board that pierces the surface it is a reversed copy, which makes the board pay two and a half times what a keel under a hull pays. It is the board, not the foil, that decides how deep a foiling boat rides.

applied · Sailing

Named alongside it

The objects these essays reach for when they reach for this one.

Induced dragModel limitThe Trefftz planeOptimisationSpan loadingBiplaneCanardDownwashNeutral pointTrimBoundary conditionCirculation

All concepts