One question, answered three times. This is not a syllabus. It is what one idea looks like at three different ages, and it is the clearest way to show how a student would be taught rather than tell you.
Grades 5 to 8
It is not the wings. It is the air.
A wing is pushed up because it pushes air down. If there is less air in each cubic metre, the wing has to move faster before there is enough of it to push, and moving faster takes runway. The propeller has the same problem, and so does the engine, which is why the effect is far larger than anyone expects.
Air thins when it is hot, and it thins when you climb. Pilots combine both into one number: the altitude the aeroplane believes it is at.
density altitude ≈ pressure altitude + 120 × (OAT - standard temperature)
Phoenix Sky Harbor sits at about 1,135 feet. On a 45 degree Celsius July afternoon the air is roughly 32 degrees warmer than standard. Manchester sits at about 257 feet, and on an 8 degree January morning the air is roughly 6.5 degrees colder than standard.
Phoenix 1,135 + (120 × 32.2) ≈ 5,000 ft
Manchester 257 - (120 × 6.5) ≈ -520 ft
The aeroplane in Phoenix believes it is a mile above the sea before it has begun to move. This is arithmetic, negative numbers and rates of change. It does not feel like any of them.
Grades 9 to 12
Derive it, then argue with it.
Lift depends on air density, on the square of speed, on wing area and on the lift coefficient.
L = ½ ρ v² S CL
At the instant of lift off, lift equals weight. Wing area is fixed. The aeroplane is rotated to a fixed attitude, so the lift coefficient is fixed too. Everything on the right except density and speed is therefore constant, which gives
vLOF ∝ 1 / √ρ
Ground roll is approximately the lift off speed squared over twice the mean acceleration. The numerator goes as one over density. And for a normally aspirated piston engine with a fixed pitch propeller, thrust falls roughly in proportion to density as well, so the denominator does too.
s = vLOF² / 2a ⇒ s ∝ 1 / σ² where σ = ρ / ρ0
In the standard atmosphere the density ratio is about 0.862 at 5,000 feet and about 1.015 at minus 520 feet. So the student rearranges and finds the answer.
sPHX / sMAN = (1.015 / 0.862)² ≈ 1.39
Thirty nine per cent more runway. Same aeroplane, same weight, same pilot, same technique.
Then the argument starts. The relationship is a square, which is why a pilot who is thirty per cent wrong about the air is nearly seventy per cent wrong about the runway, and why hot and high accidents are a category rather than a coincidence. A student who has felt that square close on them understands proportionality in a way no worksheet delivers.
Beyond the theory
The model is not what a pilot uses. That is the lesson.
No pilot computes a ground roll from first principles before taking off. They read the performance chart in the aircraft handbook, because the real aeroplane also has a propeller whose efficiency changes, a runway that may slope, a surface that may be wet grass, and a wind that may be doing something other than what the forecast said.
The derivation exists to make the chart intelligible, not to replace it. Learning when to trust your own model, and when the professional's table beats it, is the actual transferable skill, and it is the one this subject teaches better than almost any other.
Figures are standard atmosphere first order values and elevations are approximate. The aircraft's published performance chart is always the authority.