Gossamer Condor — 96 ft of wing at 11 mphvsSchempp-Hirth Standard Cirrus — 15 m, two Wortmann sections
root section l7769 → fxs02196 · tip section — → fx6617a2 · tip cap reach 0.200 → 0.450 · area 66293551 mm² → 10001997 mm² · tip chord 1431 mm → 345 mm · sweep parameter 11.711 → 2.946
units
These analyses are not directly comparable
- different trim loads (942 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.
- Gossamer Condor — 96 ft of wing at 11 mph
- Schempp-Hirth Standard Cirrus — 15 m, two Wortmann sections
What changed
| Property | Gossamer Condor | Schempp-Hirth Standar… | Change | % |
|---|---|---|---|---|
| Geometry | ||||
| Span | 29260 mm | 15000 mm | -14260 mm | -48.7% |
| Root chord | 2862 mm | 855 mm | -2007 mm | -70.1% |
| Tip chord | 1431 mm | 345 mm | -1086 mm | -75.9% |
| Sweep parameter | 11.711 | 2.946 | -8.765 | -74.8% |
| Dihedral | 3.00° | 2.00° | -1.00° | -33.3% |
| Tip twist | 0.00° | -2.00° | -2.00° | — |
| TE thickness | 2 mm | 2 mm | +1 mm | +33.3% |
| Tip cap reach | 0.200 | 0.450 | +0.250 | +125.0% |
| Derived | ||||
| Aspect ratio | 12.914 | 22.496 | +9.581 | +74.2% |
| Area | 66293551 mm² | 10001997 mm² | -56291554 mm² | -84.9% |
| Taper | 0.500 | 0.404 | -0.096 | -19.3% |
| MAC | 2358 mm | 705 mm | -1654 mm | -70.1% |
| Sections | ||||
| Root section | l7769 | fxs02196 | changed | — |
| Tip section | — | fx6617a2 | changed | — |
| Shapedeviation at matched span fractions, 64 samples | ||||
| Chord deviation (max) | 2007 mm | |||
| Chord deviation (RMS) | 1627 mm | |||
| Twist deviation (max) | 2.00° | |||
| Dihedral deviation (max) | 505 mm | |||
| Tip cap deviation (max) | 7953 mm | |||
Performance
CoefficientsDimensionless — how good the shape is, independent of size and speed.
Spanwise
withheld — “Gossamer Condor” integrates to CL 0.112 against the polar’s CL at the same α (this analysis predates the loading reporting its own) 0.539 (0.21×); “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
| CD | Gossamer Condor | Schempp-Hirth Standar… |
|---|---|---|
| 0.013 | 0.377 | 0.550 |
| 0.014 | 0.422 | 0.587 |
| 0.014 | 0.464 | 0.625 |
| 0.015 | 0.475 | 0.634 |
| 0.016 | 0.539 | 0.697 |
| 0.017 | 0.566 | 0.731 |
| 0.019 | 0.617 | 0.789 |
| 0.022 | 0.671 | 0.867 |
| 0.024 | 0.714 | 0.919 |
| 0.028 | 0.800 | 1.04 |
| 0.030 | 0.835 | 1.09 |
| 0.039 | 0.978 | 1.28 |