Schempp-Hirth Standard Cirrus — 15 m, two Wortmann sectionsvsCessna 172 Skyhawk — the most-built wing in aviation
root section fxs02196 → naca2412 · tip section fx6617a2 → — · tip chord 345 mm → 1310 mm · mac 705 mm → 1504 mm · taper 0.404 → 0.804 · root chord 855 mm → 1630 mm
units
These analyses are not directly comparable
- different trim loads (3237 N vs 10791 N) — each wing is carrying a different weight
The geometry comparison below is unaffected — it is a comparison of shapes, not of runs.
- Schempp-Hirth Standard Cirrus — 15 m, two Wortmann sections
- Cessna 172 Skyhawk — the most-built wing in aviation
What changed
| Property | Schempp-Hirth Standar… | Cessna 172 Skyhawk | Change | % |
|---|---|---|---|---|
| Geometry | ||||
| Span | 15000 mm | 11000 mm | -4000 mm | -26.7% |
| Root chord | 855 mm | 1630 mm | +775 mm | +90.6% |
| Tip chord | 345 mm | 1310 mm | +965 mm | +279.7% |
| Sweep parameter | 2.946 | 1.666 | -1.280 | -43.4% |
| Dihedral | 2.00° | 1.73° | -0.27° | -13.5% |
| Tip twist | -2.00° | -3.00° | -1.00° | +50.0% |
| TE thickness | 2 mm | 3 mm | +1 mm | +50.0% |
| Tip cap reach | 0.450 | 0.200 | -0.250 | -55.6% |
| Derived | ||||
| Aspect ratio | 22.496 | 7.350 | -15.146 | -67.3% |
| Area | 10001997 mm² | 16463140 mm² | +6461144 mm² | +64.6% |
| Taper | 0.404 | 0.804 | +0.400 | +99.2% |
| MAC | 705 mm | 1504 mm | +799 mm | +113.4% |
| Sections | ||||
| Root section | fxs02196 | naca2412 | 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 — “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×); “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×). 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) | Schempp-Hirth Standar… | Cessna 172 Skyhawk |
|---|---|---|
| 66.29 | 42.48 | 17.11 |
| 69.25 | 41.82 | 18.41 |
| 73.50 | 40.61 | 20.27 |
| 76.83 | 39.49 | 21.72 |
| 77.75 | 39.18 | 22.06 |