Cessna 172 Skyhawk — the most-built wing in aviationvsSchempp-Hirth Standard Cirrus — 15 m, two Wortmann sections
root section naca2412 → fxs02196 · tip section — → fx6617a2 · aspect ratio 7.350 → 22.496 · tip cap reach 0.200 → 0.450 · sweep parameter 1.666 → 2.946 · tip chord 1310 mm → 345 mm
units
These analyses are not directly comparable
- different trim loads (10791 N vs 3237 N) — each wing is carrying a different weight
The geometry comparison below is unaffected — it is a comparison of shapes, not of runs.
- Cessna 172 Skyhawk — the most-built wing in aviation
- Schempp-Hirth Standard Cirrus — 15 m, two Wortmann sections
What changed
| Property | Cessna 172 Skyhawk | Schempp-Hirth Standar… | Change | % |
|---|---|---|---|---|
| Geometry | ||||
| Span | 11000 mm | 15000 mm | +4000 mm | +36.4% |
| Root chord | 1630 mm | 855 mm | -775 mm | -47.5% |
| Tip chord | 1310 mm | 345 mm | -965 mm | -73.7% |
| Sweep parameter | 1.666 | 2.946 | +1.280 | +76.8% |
| Dihedral | 1.73° | 2.00° | +0.27° | +15.6% |
| Tip twist | -3.00° | -2.00° | +1.00° | -33.3% |
| TE thickness | 3 mm | 2 mm | -1 mm | -33.3% |
| Tip cap reach | 0.200 | 0.450 | +0.250 | +125.0% |
| Derived | ||||
| Aspect ratio | 7.350 | 22.496 | +15.146 | +206.1% |
| Area | 16463140 mm² | 10001997 mm² | -6461144 mm² | -39.2% |
| Taper | 0.804 | 0.404 | -0.400 | -49.8% |
| MAC | 1504 mm | 705 mm | -799 mm | -53.1% |
| Sections | ||||
| Root section | naca2412 | fxs02196 | changed | — |
| Tip section | — | fx6617a2 | changed | — |
| Shapedeviation at matched span fractions, 64 samples | ||||
| Chord deviation (max) | 965 mm | |||
| Chord deviation (RMS) | 833 mm | |||
| Twist deviation (max) | 1.00° | |||
| Dihedral deviation (max) | 107 mm | |||
| Tip cap deviation (max) | 2149 mm | |||
Performance
CoefficientsDimensionless — how good the shape is, independent of size and speed.
ForcesNewtons and watts — what each wing actually carries and costs at this condition.
Spanwise
withheld — “Cessna 172 Skyhawk” integrates to CL 0.034 against the polar’s CL at the same α (this analysis predates the loading reporting its own) 0.344 (0.10×); “Schempp-Hirth Standar…” integrates to CL 0.052 against the polar’s CL at the same α (this analysis predates the loading reporting its own) 0.541 (0.10×). A loading that does not integrate back to its own wing’s CL is not a coarse curve, it is a wrong one.
air, ρ = 1.225 kg/m³
data
| V (kt) | Cessna 172 Skyhawk | Schempp-Hirth Standar… |
|---|---|---|
| 66.29 | 17.11 | 42.48 |
| 69.25 | 18.41 | 41.82 |
| 73.50 | 20.27 | 40.61 |
| 76.83 | 21.72 | 39.49 |
| 77.75 | 22.06 | 39.18 |