S2050 8.93% (s2050-il)
S2050 8.93% - Selig S2050 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s2050-il) S2050 8.93% Selig S2050 low Reynolds number airfoil Max thickness 8.9% at 29.8% chord. Max camber 1.1% at 69.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S2050 8.93%
1.00000 0.00000
0.99673 0.00047
0.98732 0.00210
0.97251 0.00484
0.95280 0.00821
0.92826 0.01179
0.89894 0.01556
0.86520 0.01956
0.82744 0.02374
0.78613 0.02806
0.74177 0.03246
0.69492 0.03689
0.64622 0.04125
0.59626 0.04529
0.54553 0.04887
0.49454 0.05190
0.44383 0.05428
0.39393 0.05591
0.34531 0.05673
0.29847 0.05667
0.25386 0.05571
0.21189 0.05380
0.17293 0.05094
0.13731 0.04718
0.10534 0.04256
0.07728 0.03716
0.05332 0.03110
0.03363 0.02452
0.01833 0.01763
0.00756 0.01069
0.00137 0.00390
0.00034 -0.00192
0.00484 -0.00730
0.01443 -0.01287
0.02880 -0.01794
0.04792 -0.02231
0.07182 -0.02581
0.10040 -0.02854
0.13340 -0.03055
0.17052 -0.03189
0.21134 -0.03266
0.25539 -0.03289
0.30216 -0.03260
0.35111 -0.03183
0.40167 -0.03058
0.45327 -0.02884
0.50532 -0.02659
0.55720 -0.02379
0.60859 -0.02007
0.65946 -0.01567
0.70940 -0.01126
0.75762 -0.00722
0.80337 -0.00377
0.84590 -0.00106
0.88450 0.00084
0.91851 0.00190
0.94729 0.00216
0.97020 0.00173
0.98674 0.00098
0.99669 0.00030
1.00000 0.00000
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Polars for S2050 8.93% (s2050-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s2050-il | 50,000 | 9 | 33.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 50,000 | 5 | 34.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 100,000 | 9 | 48.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 100,000 | 5 | 47 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 200,000 | 9 | 63.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 200,000 | 5 | 58.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 500,000 | 9 | 80.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 500,000 | 5 | 70.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 1,000,000 | 9 | 88.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 1,000,000 | 5 | 80.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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