Piper PA-28 Cherokee — the Hershey-bar wingvsMIT Daedalus 88 — the 34 m human-powered wing
root section naca652415 → dae11 · tip section — → dae31 · aspect ratio 5.624 → 36.667 · span 9144 mm → 34100 mm · area 14868144 mm² → 31712462 mm² · dihedral 7.00° → 1.00°
units
These analyses are not directly comparable
- different trim loads (9565 N vs 1020 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
- MIT Daedalus 88 — the 34 m human-powered wing
What changed
| Property | Piper PA-28 Cherokee | MIT Daedalus 88 | Change | % |
|---|---|---|---|---|
| Geometry | ||||
| Span | 9144 mm | 34100 mm | +24956 mm | +272.9% |
| Root chord | 1626 mm | 1050 mm | -576 mm | -35.4% |
| Tip chord | 1626 mm | 762 mm | -864 mm | -53.1% |
| Sweep parameter | 0.000 | 0.484 | +0.484 | — |
| Dihedral | 7.00° | 1.00° | -6.00° | -85.7% |
| Tip twist | 0.00° | -1.50° | -1.50° | — |
| TE thickness | 3 mm | 2 mm | -2 mm | -50.0% |
| Tip cap reach | 0.300 | 0.250 | -0.050 | -16.7% |
| Derived | ||||
| Aspect ratio | 5.624 | 36.667 | +31.044 | +552.0% |
| Area | 14868144 mm² | 31712462 mm² | +16844318 mm² | +113.3% |
| Taper | 1.000 | 0.726 | -0.274 | -27.4% |
| MAC | 1626 mm | 939 mm | -687 mm | -42.2% |
| Sections | ||||
| Root section | naca652415 | dae11 | changed | — |
| Tip section | — | dae31 | changed | — |
| Shapedeviation at matched span fractions, 64 samples | ||||
| Chord deviation (max) | 864 mm | |||
| Chord deviation (RMS) | 703 mm | |||
| Twist deviation (max) | 1.50° | |||
| Dihedral deviation (max) | 264 mm | |||
| Tip cap deviation (max) | 12503 mm | |||
Performance
CoefficientsDimensionless — how good the shape is, independent of size and speed.
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×); “MIT Daedalus 88” integrates to CL 0.120 against the polar’s CL at the same α (this analysis predates the loading reporting its own) 0.913 (0.13×). 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
| CD | Piper PA-28 Cherokee | MIT Daedalus 88 |
|---|---|---|
| 0.012 | 0.344 | 0.444 |
| 0.013 | 0.352 | 0.492 |
| 0.013 | 0.362 | 0.549 |
| 0.014 | 0.371 | 0.591 |
| 0.014 | 0.375 | 0.616 |
| 0.015 | 0.389 | 0.697 |
| 0.016 | 0.410 | 0.794 |
| 0.018 | 0.443 | 0.890 |
| 0.019 | 0.449 | 0.913 |
| 0.023 | 0.506 | 1.06 |
| 0.025 | 0.537 | 1.13 |
| 0.029 | 0.580 | 1.25 |
| 0.037 | 0.666 | 1.43 |
| 0.039 | 0.687 | 1.49 |