S8055 (12%) (s8055-il)
S8055 (12%) - Selig S8055 (12%) low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s8055-il) S8055 (12%) Selig S8055 (12%) low Reynolds number airfoil Max thickness 12% at 33.9% chord. Max camber 1.6% at 44.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S8055 (12%)
1.00000 .00000
.99796 .00016
.99197 .00081
.98231 .00211
.96923 .00407
.95291 .00666
.93354 .00991
.91134 .01383
.88661 .01841
.85963 .02358
.83070 .02924
.80014 .03529
.76823 .04155
.73528 .04781
.70158 .05372
.66703 .05899
.63153 .06368
.59535 .06781
.55865 .07137
.52163 .07437
.48451 .07677
.44749 .07856
.41079 .07974
.37459 .08026
.33907 .08016
.30446 .07945
.27093 .07812
.23870 .07622
.20796 .07375
.17888 .07072
.15166 .06715
.12643 .06303
.10331 .05840
.08246 .05320
.06388 .04745
.04757 .04130
.03364 .03479
.02208 .02803
.01306 .02119
.00649 .01419
.00215 .00725
.00003 .00086
.00075 -.00429
.00499 -.00859
.01260 -.01287
.02322 -.01701
.03674 -.02091
.05304 -.02451
.07204 -.02777
.09363 -.03066
.11770 -.03316
.14412 -.03527
.17273 -.03697
.20339 -.03829
.23590 -.03921
.27007 -.03977
.30570 -.03996
.34256 -.03982
.38042 -.03936
.41905 -.03858
.45818 -.03753
.49755 -.03619
.53692 -.03458
.57599 -.03267
.61458 -.03039
.65253 -.02777
.68967 -.02481
.72588 -.02162
.76098 -.01832
.79475 -.01508
.82692 -.01207
.85715 -.00939
.88513 -.00708
.91058 -.00516
.93322 -.00362
.95281 -.00242
.96917 -.00144
.98224 -.00065
.99193 -.00014
.99795 .00002
1.00000 .00000
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Polars for S8055 (12%) (s8055-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8055-il | 50,000 | 9 | 32.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 50,000 | 5 | 32.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 100,000 | 9 | 50.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 100,000 | 5 | 48.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 200,000 | 9 | 71 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 200,000 | 5 | 62.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 500,000 | 9 | 86.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 500,000 | 5 | 74.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 1,000,000 | 9 | 95 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 1,000,000 | 5 | 88.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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