S7055 (10.5%) Flat-Bottomed (s7055-il)
S7055 (10.5%) Flat-Bottomed - Selig S7055 low Reynolds number airfoil
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(s7055-il) S7055 (10.5%) Flat-Bottomed Selig S7055 low Reynolds number airfoil Max thickness 10.5% at 31.8% chord. Max camber 3.3% at 38.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S7055 (10.5%) Flat-Bottomed 1.00000 0.00000 0.99808 0.00023 0.99243 0.00104 0.98327 0.00251 0.97083 0.00464 0.95526 0.00738 0.93671 0.01073 0.91539 0.01470 0.89155 0.01924 0.86543 0.02431 0.83728 0.02981 0.80738 0.03565 0.77601 0.04169 0.74337 0.04770 0.70958 0.05354 0.67484 0.05920 0.63934 0.06454 0.60327 0.06949 0.56688 0.07399 0.53032 0.07791 0.49374 0.08125 0.45740 0.08391 0.42142 0.08584 0.38601 0.08706 0.35133 0.08749 0.31754 0.08713 0.28483 0.08599 0.25332 0.08404 0.22311 0.08132 0.19440 0.07787 0.16729 0.07370 0.14189 0.06891 0.11833 0.06352 0.09668 0.05760 0.07705 0.05125 0.05952 0.04455 0.04413 0.03761 0.03097 0.03054 0.02008 0.02346 0.01148 0.01655 0.00524 0.00998 0.00139 0.00398 0.00007 -0.00091 0.00214 -0.00493 0.00762 -0.00871 0.01587 -0.01193 0.02720 -0.01436 0.04175 -0.01620 0.05938 -0.01763 0.07995 -0.01870 0.10333 -0.01944 0.12935 -0.01989 0.15784 -0.02009 0.18857 -0.02006 0.22132 -0.01980 0.25590 -0.01927 0.29218 -0.01849 0.32993 -0.01757 0.36889 -0.01656 0.40878 -0.01551 0.44933 -0.01445 0.49021 -0.01338 0.53116 -0.01230 0.57188 -0.01123 0.61212 -0.01018 0.65160 -0.00914 0.69009 -0.00813 0.72734 -0.00716 0.76303 -0.00622 0.79681 -0.00533 0.82841 -0.00450 0.85793 -0.00373 0.88544 -0.00301 0.91063 -0.00235 0.93322 -0.00175 0.95293 -0.00124 0.96949 -0.00080 0.98266 -0.00046 0.99224 -0.00020 0.99805 -0.00005 1.00000 0.00000 |
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Polars for S7055 (10.5%) Flat-Bottomed (s7055-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s7055-il | 50,000 | 9 | 31.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 50,000 | 5 | 36.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 100,000 | 9 | 54.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 100,000 | 5 | 56.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 200,000 | 9 | 77.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 200,000 | 5 | 75.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 500,000 | 9 | 107.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 500,000 | 5 | 99.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 1,000,000 | 9 | 129.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 1,000,000 | 5 | 116.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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