S2062 8% (s2062-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2062 8% (s2062-il) Reynolds number: 100,000 Max Cl/Cd: 52.89 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2062-il-100000.txt Download as CSV file: xf-s2062-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S2062 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4806 0.09678 0.09181 -0.0193 1.0000 0.0990
-8.500 -0.4860 0.09348 0.08859 -0.0220 1.0000 0.1031
-8.250 -0.5145 0.09063 0.08592 -0.0294 1.0000 0.1050
-8.000 -0.5085 0.08588 0.08121 -0.0284 1.0000 0.1067
-7.750 -0.4872 0.08307 0.07836 -0.0242 1.0000 0.1119
-7.500 -0.4961 0.07953 0.07491 -0.0274 1.0000 0.1162
-7.250 -0.5233 0.07422 0.06950 -0.0393 1.0000 0.1194
-7.000 -0.4980 0.07157 0.06704 -0.0311 1.0000 0.1237
-6.750 -0.5112 0.06745 0.06269 -0.0388 1.0000 0.1327
-6.500 -0.4971 0.06384 0.05928 -0.0344 1.0000 0.1366
-6.250 -0.5015 0.04646 0.04078 -0.0439 1.0000 0.0639
-6.000 -0.4910 0.04223 0.03638 -0.0432 1.0000 0.0617
-5.750 -0.4791 0.03756 0.03128 -0.0425 1.0000 0.0591
-5.500 -0.4628 0.03206 0.02462 -0.0413 1.0000 0.0534
-5.250 -0.4428 0.02938 0.02144 -0.0400 1.0000 0.0528
-5.000 -0.4225 0.02606 0.01768 -0.0390 1.0000 0.0534
-4.750 -0.4009 0.02356 0.01499 -0.0380 1.0000 0.0560
-4.500 -0.3782 0.02198 0.01317 -0.0369 1.0000 0.0621
-4.250 -0.3555 0.02039 0.01145 -0.0359 1.0000 0.0729
-4.000 -0.3322 0.01876 0.00975 -0.0348 1.0000 0.0941
-3.750 -0.3100 0.01782 0.00889 -0.0341 1.0000 0.1307
-3.500 -0.2875 0.01685 0.00806 -0.0333 1.0000 0.1656
-3.250 -0.2646 0.01596 0.00731 -0.0325 1.0000 0.2049
-3.000 -0.2420 0.01512 0.00672 -0.0318 1.0000 0.2607
-2.750 -0.2200 0.01417 0.00630 -0.0310 1.0000 0.3511
-2.500 -0.2002 0.01315 0.00610 -0.0296 1.0000 0.5114
-2.250 -0.1881 0.01247 0.00627 -0.0254 1.0000 0.7183
-2.000 -0.1780 0.01226 0.00637 -0.0202 1.0000 0.8704
-1.750 -0.1290 0.01210 0.00599 -0.0241 1.0000 1.0000
-1.500 -0.1082 0.01217 0.00582 -0.0236 1.0000 1.0000
-1.250 -0.0870 0.01229 0.00572 -0.0231 1.0000 1.0000
-1.000 -0.0657 0.01245 0.00570 -0.0226 1.0000 1.0000
-0.750 -0.0443 0.01264 0.00571 -0.0222 1.0000 1.0000
-0.500 -0.0231 0.01287 0.00580 -0.0217 1.0000 1.0000
-0.250 -0.0021 0.01314 0.00595 -0.0213 1.0000 1.0000
0.000 0.0187 0.01344 0.00615 -0.0209 1.0000 1.0000
0.250 0.0503 0.01387 0.00648 -0.0227 0.9961 1.0000
0.500 0.1005 0.01443 0.00697 -0.0278 0.9852 1.0000
0.750 0.1490 0.01487 0.00736 -0.0325 0.9734 1.0000
1.000 0.1966 0.01522 0.00769 -0.0369 0.9609 1.0000
1.250 0.2440 0.01547 0.00795 -0.0410 0.9480 1.0000
1.500 0.2916 0.01562 0.00814 -0.0450 0.9345 1.0000
1.750 0.3396 0.01564 0.00824 -0.0488 0.9208 1.0000
2.000 0.3889 0.01554 0.00822 -0.0526 0.9071 1.0000
2.250 0.4380 0.01530 0.00811 -0.0561 0.8930 1.0000
2.500 0.4824 0.01499 0.00794 -0.0583 0.8774 1.0000
2.750 0.5236 0.01462 0.00769 -0.0597 0.8605 1.0000
3.000 0.5584 0.01428 0.00747 -0.0597 0.8402 1.0000
3.250 0.5904 0.01394 0.00726 -0.0591 0.8171 1.0000
3.500 0.6183 0.01370 0.00709 -0.0577 0.7896 1.0000
3.750 0.6450 0.01350 0.00693 -0.0561 0.7581 1.0000
4.000 0.6697 0.01342 0.00688 -0.0543 0.7204 1.0000
4.250 0.6939 0.01345 0.00691 -0.0524 0.6773 1.0000
4.500 0.7167 0.01363 0.00700 -0.0505 0.6271 1.0000
4.750 0.7384 0.01396 0.00718 -0.0485 0.5698 1.0000
5.000 0.7585 0.01445 0.00745 -0.0464 0.5060 1.0000
5.250 0.7762 0.01511 0.00781 -0.0442 0.4271 1.0000
5.500 0.7919 0.01601 0.00822 -0.0420 0.3348 1.0000
5.750 0.8086 0.01708 0.00888 -0.0403 0.2453 1.0000
6.000 0.8185 0.01950 0.01035 -0.0378 0.1181 1.0000
6.250 0.8333 0.02161 0.01211 -0.0356 0.0792 1.0000
6.500 0.8527 0.02330 0.01376 -0.0340 0.0681 1.0000
6.750 0.8742 0.02545 0.01582 -0.0329 0.0624 1.0000
7.000 0.9001 0.02737 0.01793 -0.0320 0.0591 1.0000
7.250 0.9260 0.02955 0.02031 -0.0312 0.0565 1.0000
7.500 0.9492 0.03174 0.02258 -0.0306 0.0528 1.0000
7.750 0.9712 0.03545 0.02652 -0.0299 0.0508 1.0000
8.000 0.9905 0.03865 0.03018 -0.0285 0.0506 1.0000
8.250 1.0067 0.04261 0.03457 -0.0270 0.0508 1.0000
8.500 1.0221 0.04591 0.03834 -0.0253 0.0516 1.0000
8.750 1.0213 0.05041 0.04395 -0.0215 0.0556 1.0000
9.000 1.0191 0.05613 0.05020 -0.0193 0.0592 1.0000
9.250 1.0214 0.06158 0.05589 -0.0181 0.0618 1.0000
9.500 0.9333 0.05875 0.05398 -0.0108 0.0664 1.0000
9.750 0.8975 0.06377 0.05924 -0.0086 0.0677 1.0000
10.000 0.8648 0.06915 0.06477 -0.0089 0.0682 1.0000
10.250 0.8310 0.07592 0.07165 -0.0117 0.0682 1.0000
10.500 0.7923 0.08553 0.08134 -0.0179 0.0686 1.0000
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Polar data table (+)
Polar graphs
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