Schempp-Hirth Standard Cirrus — 15 m, two Wortmann sectionsvsGossamer Condor — 96 ft of wing at 11 mph
root section fxs02196 → l7769 · tip section fx6617a2 → — · area 10001997 mm² → 66293551 mm² · tip chord 345 mm → 1431 mm · sweep parameter 2.946 → 11.711 · root chord 855 mm → 2862 mm
units
These analyses are not directly comparable
- different trim loads (3237 N vs 942 N) — each wing is carrying a different weight
The geometry comparison below is unaffected — it is a comparison of shapes, not of runs.
- Schempp-Hirth Standard Cirrus — 15 m, two Wortmann sections
- Gossamer Condor — 96 ft of wing at 11 mph
What changed
| Property | Schempp-Hirth Standar… | Gossamer Condor | Change | % |
|---|---|---|---|---|
| Geometry | ||||
| Span | 15000 mm | 29260 mm | +14260 mm | +95.1% |
| Root chord | 855 mm | 2862 mm | +2007 mm | +234.7% |
| Tip chord | 345 mm | 1431 mm | +1086 mm | +314.8% |
| Sweep parameter | 2.946 | 11.711 | +8.765 | +297.5% |
| Dihedral | 2.00° | 3.00° | +1.00° | +50.0% |
| Tip twist | -2.00° | 0.00° | +2.00° | -100.0% |
| TE thickness | 2 mm | 2 mm | -1 mm | -25.0% |
| Tip cap reach | 0.450 | 0.200 | -0.250 | -55.6% |
| Derived | ||||
| Aspect ratio | 22.496 | 12.914 | -9.581 | -42.6% |
| Area | 10001997 mm² | 66293551 mm² | +56291554 mm² | +562.8% |
| Taper | 0.404 | 0.500 | +0.096 | +23.9% |
| MAC | 705 mm | 2358 mm | +1654 mm | +234.6% |
| Sections | ||||
| Root section | fxs02196 | l7769 | 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 — “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×); “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×). 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 | Schempp-Hirth Standar… | Gossamer Condor |
|---|---|---|
| 0.013 | 0.550 | 0.377 |
| 0.014 | 0.587 | 0.422 |
| 0.014 | 0.625 | 0.464 |
| 0.015 | 0.634 | 0.475 |
| 0.016 | 0.697 | 0.539 |
| 0.017 | 0.731 | 0.566 |
| 0.019 | 0.789 | 0.617 |
| 0.022 | 0.867 | 0.671 |
| 0.024 | 0.919 | 0.714 |
| 0.028 | 1.04 | 0.800 |
| 0.030 | 1.09 | 0.835 |
| 0.039 | 1.28 | 0.978 |