Piper PA-28 Cherokee — the Hershey-bar wingvsSchempp-Hirth Standard Cirrus — 15 m, two Wortmann sections
root section naca652415 → fxs02196 · tip section — → fx6617a2 · aspect ratio 5.624 → 22.496 · tip chord 1626 mm → 345 mm · dihedral 7.00° → 2.00° · span 9144 mm → 15000 mm
units
These analyses are not directly comparable
- different trim loads (9565 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.
- Piper PA-28 Cherokee — the Hershey-bar wing
- Schempp-Hirth Standard Cirrus — 15 m, two Wortmann sections
What changed
| Property | Piper PA-28 Cherokee | Schempp-Hirth Standar… | Change | % |
|---|---|---|---|---|
| Geometry | ||||
| Span | 9144 mm | 15000 mm | +5856 mm | +64.0% |
| Root chord | 1626 mm | 855 mm | -771 mm | -47.4% |
| Tip chord | 1626 mm | 345 mm | -1281 mm | -78.8% |
| Sweep parameter | 0.000 | 2.946 | +2.946 | — |
| Dihedral | 7.00° | 2.00° | -5.00° | -71.4% |
| Tip twist | 0.00° | -2.00° | -2.00° | — |
| TE thickness | 3 mm | 2 mm | -1 mm | -33.3% |
| Tip cap reach | 0.300 | 0.450 | +0.150 | +50.0% |
| Derived | ||||
| Aspect ratio | 5.624 | 22.496 | +16.872 | +300.0% |
| Area | 14868144 mm² | 10001997 mm² | -4866147 mm² | -32.7% |
| Taper | 1.000 | 0.404 | -0.596 | -59.6% |
| MAC | 1626 mm | 705 mm | -921 mm | -56.7% |
| Sections | ||||
| Root section | naca652415 | fxs02196 | changed | — |
| Tip section | — | fx6617a2 | changed | — |
| Shapedeviation at matched span fractions, 64 samples | ||||
| Chord deviation (max) | 1281 mm | |||
| Chord deviation (RMS) | 974 mm | |||
| Twist deviation (max) | 2.00° | |||
| Dihedral deviation (max) | 299 mm | |||
| Tip cap deviation (max) | 3101 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 — “Piper PA-28 Cherokee” integrates to CL 0.007 against the polar’s CL at the same α (this analysis predates the loading reporting its own) 0.271 (0.03×); “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) | Piper PA-28 Cherokee | Schempp-Hirth Standar… |
|---|---|---|
| 59.40 | 11.06 | 43.23 |
| 60.75 | 11.54 | 43.27 |
| 65.00 | 13.05 | 42.76 |
| 68.12 | 14.15 | 42.07 |
| 69.25 | 14.68 | 41.82 |
| 73.50 | 16.66 | 40.61 |
| 76.85 | 18.21 | 39.49 |
| 77.75 | 18.56 | 39.18 |