MIT Daedalus 88 — the 34 m human-powered wingvsPiper PA-28 Cherokee — the Hershey-bar wing
root section dae11 → naca652415 · tip section dae31 → — · dihedral 1.00° → 7.00° · tip chord 762 mm → 1626 mm · sweep parameter 0.484 → 0.000 · tip twist -1.50° → 0.00°
units
These analyses are not directly comparable
- different trim loads (1020 N vs 9565 N) — each wing is carrying a different weight
The geometry comparison below is unaffected — it is a comparison of shapes, not of runs.
- MIT Daedalus 88 — the 34 m human-powered wing
- Piper PA-28 Cherokee — the Hershey-bar wing
What changed
| Property | MIT Daedalus 88 | Piper PA-28 Cherokee | Change | % |
|---|---|---|---|---|
| Geometry | ||||
| Span | 34100 mm | 9144 mm | -24956 mm | -73.2% |
| Root chord | 1050 mm | 1626 mm | +576 mm | +54.9% |
| Tip chord | 762 mm | 1626 mm | +864 mm | +113.4% |
| Sweep parameter | 0.484 | 0.000 | -0.484 | -100.0% |
| Dihedral | 1.00° | 7.00° | +6.00° | +600.0% |
| Tip twist | -1.50° | 0.00° | +1.50° | -100.0% |
| TE thickness | 2 mm | 3 mm | +2 mm | +100.0% |
| Tip cap reach | 0.250 | 0.300 | +0.050 | +20.0% |
| Derived | ||||
| Aspect ratio | 36.667 | 5.624 | -31.044 | -84.7% |
| Area | 31712462 mm² | 14868144 mm² | -16844318 mm² | -53.1% |
| Taper | 0.726 | 1.000 | +0.274 | +37.8% |
| MAC | 939 mm | 1626 mm | +687 mm | +73.1% |
| Sections | ||||
| Root section | dae11 | naca652415 | 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 — “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×); “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×). 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 | MIT Daedalus 88 | Piper PA-28 Cherokee |
|---|---|---|
| 0.012 | 0.444 | 0.344 |
| 0.013 | 0.492 | 0.352 |
| 0.013 | 0.549 | 0.362 |
| 0.014 | 0.591 | 0.371 |
| 0.014 | 0.616 | 0.375 |
| 0.015 | 0.697 | 0.389 |
| 0.016 | 0.794 | 0.410 |
| 0.018 | 0.890 | 0.443 |
| 0.019 | 0.913 | 0.449 |
| 0.023 | 1.06 | 0.506 |
| 0.025 | 1.13 | 0.537 |
| 0.029 | 1.25 | 0.580 |
| 0.037 | 1.43 | 0.666 |
| 0.039 | 1.49 | 0.687 |