S2050 8.93% (s2050-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 100,000 Max Cl/Cd: 48.78 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2050-il-100000.txt Download as CSV file: xf-s2050-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S2050 8.93%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5099 0.10065 0.09556 -0.0162 1.0000 0.1126
-9.000 -0.5421 0.09710 0.09218 -0.0244 1.0000 0.1162
-8.750 -0.5337 0.09214 0.08726 -0.0233 1.0000 0.1179
-8.500 -0.5167 0.08889 0.08398 -0.0206 1.0000 0.1210
-8.250 -0.5170 0.08543 0.08057 -0.0213 1.0000 0.1243
-7.750 -0.5631 0.07547 0.07080 -0.0324 1.0000 0.1319
-7.500 -0.5501 0.07214 0.06751 -0.0300 1.0000 0.1341
-7.250 -0.5940 0.05017 0.04439 -0.0428 1.0000 0.0615
-7.000 -0.5854 0.04547 0.03956 -0.0424 1.0000 0.0593
-6.750 -0.5763 0.04037 0.03403 -0.0421 1.0000 0.0568
-6.500 -0.5635 0.03527 0.02829 -0.0415 1.0000 0.0550
-6.250 -0.5457 0.03147 0.02389 -0.0407 1.0000 0.0552
-6.000 -0.5250 0.02893 0.02092 -0.0399 1.0000 0.0588
-5.750 -0.5026 0.02638 0.01776 -0.0389 1.0000 0.0634
-5.500 -0.4803 0.02424 0.01557 -0.0381 1.0000 0.0695
-5.250 -0.4571 0.02248 0.01364 -0.0373 1.0000 0.0809
-5.000 -0.4337 0.02113 0.01218 -0.0365 1.0000 0.0982
-4.750 -0.4101 0.01989 0.01082 -0.0358 1.0000 0.1182
-4.500 -0.3869 0.01880 0.00983 -0.0351 1.0000 0.1386
-4.250 -0.3630 0.01775 0.00877 -0.0343 1.0000 0.1609
-4.000 -0.3393 0.01682 0.00793 -0.0337 1.0000 0.1877
-3.750 -0.3160 0.01585 0.00722 -0.0330 1.0000 0.2213
-3.500 -0.2925 0.01489 0.00656 -0.0325 1.0000 0.2732
-3.250 -0.2697 0.01361 0.00602 -0.0320 1.0000 0.3817
-3.000 -0.2537 0.01267 0.00624 -0.0292 1.0000 0.6003
-2.750 -0.2380 0.01278 0.00651 -0.0256 1.0000 0.7025
-2.500 -0.2233 0.01292 0.00666 -0.0221 1.0000 0.7572
-2.250 -0.2113 0.01303 0.00678 -0.0179 1.0000 0.7964
-2.000 -0.2008 0.01308 0.00684 -0.0137 1.0000 0.8316
-1.750 -0.1922 0.01309 0.00684 -0.0091 1.0000 0.8644
-1.500 -0.1832 0.01304 0.00678 -0.0048 1.0000 0.8986
-1.250 -0.1657 0.01297 0.00668 -0.0023 1.0000 0.9368
-1.000 -0.1107 0.01303 0.00661 -0.0074 1.0000 0.9777
-0.750 -0.0740 0.01299 0.00647 -0.0107 1.0000 1.0000
-0.500 -0.0633 0.01298 0.00638 -0.0097 1.0000 1.0000
-0.250 -0.0432 0.01313 0.00643 -0.0102 1.0000 1.0000
0.000 -0.0034 0.01354 0.00674 -0.0141 0.9942 1.0000
0.250 0.0514 0.01396 0.00708 -0.0202 0.9815 1.0000
0.500 0.1045 0.01424 0.00731 -0.0259 0.9678 1.0000
0.750 0.1557 0.01439 0.00743 -0.0309 0.9535 1.0000
1.000 0.2058 0.01442 0.00746 -0.0355 0.9387 1.0000
1.250 0.2561 0.01434 0.00741 -0.0398 0.9237 1.0000
1.500 0.3076 0.01414 0.00727 -0.0441 0.9090 1.0000
1.750 0.3585 0.01384 0.00703 -0.0479 0.8935 1.0000
2.000 0.4063 0.01349 0.00675 -0.0510 0.8759 1.0000
2.250 0.4489 0.01319 0.00652 -0.0529 0.8547 1.0000
2.500 0.4873 0.01297 0.00632 -0.0539 0.8298 1.0000
2.750 0.5196 0.01289 0.00623 -0.0539 0.8011 1.0000
3.000 0.5492 0.01291 0.00623 -0.0534 0.7703 1.0000
3.250 0.5753 0.01304 0.00632 -0.0524 0.7363 1.0000
3.500 0.6011 0.01321 0.00641 -0.0513 0.7014 1.0000
3.750 0.6260 0.01343 0.00654 -0.0501 0.6649 1.0000
4.000 0.6501 0.01368 0.00672 -0.0488 0.6262 1.0000
4.250 0.6737 0.01397 0.00691 -0.0475 0.5852 1.0000
4.500 0.6969 0.01433 0.00715 -0.0462 0.5425 1.0000
4.750 0.7195 0.01475 0.00742 -0.0449 0.4978 1.0000
5.000 0.7415 0.01524 0.00777 -0.0435 0.4513 1.0000
5.250 0.7630 0.01581 0.00817 -0.0422 0.4023 1.0000
5.500 0.7839 0.01647 0.00865 -0.0409 0.3518 1.0000
5.750 0.8043 0.01726 0.00922 -0.0396 0.3008 1.0000
6.000 0.8240 0.01821 0.00996 -0.0383 0.2496 1.0000
6.250 0.8430 0.01933 0.01082 -0.0370 0.1989 1.0000
6.500 0.8615 0.02059 0.01183 -0.0358 0.1534 1.0000
6.750 0.8798 0.02211 0.01312 -0.0345 0.1181 1.0000
7.000 0.8990 0.02397 0.01476 -0.0332 0.0947 1.0000
7.250 0.9205 0.02577 0.01658 -0.0322 0.0796 1.0000
7.500 0.9438 0.02754 0.01840 -0.0313 0.0709 1.0000
7.750 0.9687 0.03016 0.02116 -0.0306 0.0662 1.0000
8.000 0.9921 0.03236 0.02366 -0.0297 0.0621 1.0000
8.250 1.0135 0.03451 0.02586 -0.0291 0.0578 1.0000
8.500 1.0323 0.03820 0.02987 -0.0281 0.0559 1.0000
8.750 1.0474 0.04138 0.03362 -0.0265 0.0552 1.0000
9.000 1.0587 0.04511 0.03786 -0.0247 0.0550 1.0000
9.250 1.0658 0.04932 0.04255 -0.0229 0.0552 1.0000
9.500 1.0695 0.05397 0.04761 -0.0212 0.0556 1.0000
9.750 1.0691 0.05877 0.05276 -0.0196 0.0559 1.0000
10.000 1.0657 0.06377 0.05807 -0.0182 0.0562 1.0000
10.250 1.0604 0.06864 0.06322 -0.0170 0.0565 1.0000
10.500 1.0473 0.07177 0.06668 -0.0152 0.0569 1.0000
10.750 0.8582 0.07520 0.07098 -0.0136 0.0624 1.0000
11.000 0.8134 0.08643 0.08231 -0.0207 0.0641 1.0000
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Polar data table (+)
Polar graphs
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