Drela SuperGee II — a 1.5 m discus-launch glider, drawn to the planvsMIT Daedalus 88 — the 34 m human-powered wing
root section ag455ct02r → dae11 · tip section ag47ct02r → dae31 · area 218576 mm² → 31712462 mm² · span 1498 mm → 34100 mm · tip chord 94 mm → 762 mm · mac 151 mm → 939 mm
units
These analyses are not directly comparable
- different trim loads (2 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.
- Drela SuperGee II — a 1.5 m discus-launch glider, drawn to the plan
- MIT Daedalus 88 — the 34 m human-powered wing
What changed
| Property | Drela SuperGee II | MIT Daedalus 88 | Change | % |
|---|---|---|---|---|
| Geometry | ||||
| Span | 1498 mm | 34100 mm | +32602 mm | +2176.4% |
| Root chord | 183 mm | 1050 mm | +867 mm | +473.8% |
| Tip chord | 94 mm | 762 mm | +668 mm | +710.6% |
| Sweep parameter | 3.400 | 0.484 | -2.916 | -85.8% |
| Dihedral | 4.00° | 1.00° | -3.00° | -75.0% |
| Tip twist | 0.00° | -1.50° | -1.50° | — |
| TE thickness | 0 mm | 2 mm | +1 mm | +400.0% |
| Sections | 30 | 40 | +10 | +33.3% |
| Tip cap reach | 0.400 | 0.250 | -0.150 | -37.5% |
| Derived | ||||
| Aspect ratio | 10.266 | 36.667 | +26.401 | +257.2% |
| Area | 218576 mm² | 31712462 mm² | +31493886 mm² | +14408.7% |
| Taper | 0.514 | 0.726 | +0.212 | +41.3% |
| MAC | 151 mm | 939 mm | +788 mm | +520.0% |
| Sections | ||||
| Root section | ag455ct02r | dae11 | changed | — |
| Tip section | ag47ct02r | dae31 | changed | — |
| Shapedeviation at matched span fractions, 64 samples | ||||
| Chord deviation (max) | 867 mm | |||
| Chord deviation (RMS) | 786 mm | |||
| Twist deviation (max) | 1.50° | |||
| Dihedral deviation (max) | 245 mm | |||
| Tip cap deviation (max) | 16382 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 — “Drela SuperGee II” integrates to CL 0.056 against the polar’s CL at the same α (this analysis predates the loading reporting its own) 0.371 (0.15×); “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
| V (kt) | Drela SuperGee II | MIT Daedalus 88 |
|---|---|---|
| 11.54 | 19.02 | 37.99 |
| 12.15 | 19.30 | 41.06 |
| 12.61 | 19.33 | 43.38 |
| 13.00 | 19.35 | 44.69 |
| 13.68 | 19.16 | 46.93 |
| 13.85 | 19.11 | 47.31 |
| 14.70 | 18.62 | 49.17 |
| 14.74 | 18.59 | 49.26 |
| 15.55 | 17.97 | 49.22 |